Safran Helicopter Engines

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New (last 4 weeks) 11
2024 June (MTD) 6
2024 May 8
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IPC Class
B64D 27/24 - Aircraft characterised by the type or position of power plant using steam, electricity, or spring force 44
F02C 3/10 - Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor with another turbine driving an output shaft but not driving the compressor 44
F02C 7/32 - Arrangement, mounting, or driving, of auxiliaries 41
F02C 7/36 - Power transmission between the different shafts of the gas-turbine plant, or between the gas-turbine plant and the power user 38
B64D 35/08 - Transmitting power from power plant to propellers or rotors; Arrangements of transmissions characterised by the transmission being driven by a plurality of power plants 35
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NICE Class
07 - Machines and machine tools 29
37 - Construction and mining; installation and repair services 28
42 - Scientific, technological and industrial services, research and design 27
12 - Land, air and water vehicles; parts of land vehicles 26
09 - Scientific and electric apparatus and instruments 25
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Status
Pending 118
Registered / In Force 571
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1.

TURBINE ENGINE COMPRISING AN IMMOBILISING MAGNETIC COUPLING DEVICE

      
Application Number FR2023051914
Publication Number 2024/121495
Status In Force
Filing Date 2023-12-04
Publication Date 2024-06-13
Owner SAFRAN HELICOPTER ENGINES (France)
Inventor
  • Douillard, Stéphane Albert André
  • Beddok, Stéphane Meyer
  • Auduberteau, Alexandre
  • Cladiere, Mathieu Pierre

Abstract

The invention relates to a turbine engine (10) for an aircraft, comprising: - a rotating element (14) which is rotatably mounted in a structural element (12) and is intended to generate thrust during the rotation thereof; and - controlled means for immobilising the rotating element (14) with respect to the structural element (12); characterised in that the controlled immobilisation means are formed by a magnetic coupling device (42) that comprises: - a rotor (44) which is coupled with the rotating element (14) and comprises first magnetic elements (46); - a stator (52) which is stationary with respect to the structural element (12) and comprises second magnetic elements (54); the magnetic coupling device (42) being controlled between an inoperative state, in which the rotor (44) is free to rotate with respect to the stator (52), and an operative state, in which the rotor (44) is rotatably immobilised by an immobilisation resisting torque.

IPC Classes  ?

  • B64C 27/14 - Direct drive between power plant and rotor hub
  • B64D 35/00 - Transmitting power from power plant to propellers or rotors; Arrangements of transmissions
  • F02C 6/20 - Adaptations of gas-turbine plants for driving vehicles
  • F02C 7/36 - Power transmission between the different shafts of the gas-turbine plant, or between the gas-turbine plant and the power user
  • H02K 49/10 - Dynamo-electric clutches; Dynamo-electric brakes of the permanent-magnet type

2.

METHOD AND SYSTEM FOR CONTROLLING THE PERMEABILITY OF A LUBRICATION CIRCUIT OF AN AIRCRAFT TURBOMACHINE

      
Application Number EP2023084661
Publication Number 2024/121289
Status In Force
Filing Date 2023-12-07
Publication Date 2024-06-13
Owner SAFRAN HELICOPTER ENGINES (France)
Inventor
  • Benard, Mathieu
  • Piquer, Fabrice
  • Debat, Alexandre Paul Raimond
  • Laucaigne, Mathieu
  • Branchereau, Emmanuel

Abstract

The invention relates to a method for controlling the permeability of a lubrication circuit for an aircraft turbomachine, the turbomachine comprising at least one guide bearing, the lubrication circuit being configured to circulate an oil flow from upstream to downstream between an oil inlet and an oil outlet for lubricating the guide bearing, the method comprising the steps of: measuring a first temperature (T1) of the oil upstream of the guide bearing; measuring a second temperature (T2) of the oil downstream of the guide bearing; calculating a temperature difference between the second temperature (T2) and the first temperature (T1); comparing the temperature difference (ΔT) with a predetermined expected temperature difference (ΔT0); and, when the temperature difference (ΔT) is greater than the expected temperature difference (ΔT0), signalling a permeability fault in the lubrication circuit.

IPC Classes  ?

  • B64F 5/60 - Testing or inspecting aircraft components or systems
  • F01D 21/00 - Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
  • F01D 25/18 - Lubricating arrangements
  • F01D 25/20 - Lubricating arrangements using lubrication pumps
  • F02C 7/06 - Arrangement of bearings; Lubricating
  • F16N 29/04 - Special means in lubricating arrangements or systems providing for the indication or detection of undesired conditions; Use of devices responsive to conditions in lubricating arrangements or systems enabling moving parts to be stopped
  • G01K 3/14 - Thermometers giving results other than momentary value of temperature giving differentiated values in respect of space
  • G01M 15/14 - Testing gas-turbine engines or jet-propulsion engines

3.

DEVICE FOR CONTROLLING A LEAST ONE ELECTRIC MOTOR FOR AN AIRCRAFT-PROPELLING ASSEMBLY

      
Application Number 18285667
Status Pending
Filing Date 2022-04-05
First Publication Date 2024-06-06
Owner
  • SAFRAN HELICOPTER ENGINES (France)
  • SAFRAN ELECTRICAL & POWER (France)
Inventor
  • Beddok, Stéphane Meyer
  • Lemay, David Bernard Martin
  • Bambaud, Julien Marc Nicolas

Abstract

The present invention relates to a device (1) for controlling an electric aircraft-propelling assembly, said propelling assembly comprising a propeller (3) and at least one electric motor (4) that is powered by an electric supply voltage and that delivers a torque and a rotation speed to drive the propeller (3). The control device (1) comprises at least a unit (11) for measuring an electric supply voltage, and a control unit (12) suitable for making a signal delivered to the electric motor vary as a function of said electric supply voltage, with a view to making the rotation speed of the propeller vary.

IPC Classes  ?

  • H02P 29/10 - Arrangements for regulating or controlling electric motors, appropriate for both AC and DC motors for preventing overspeed or under speed
  • B64C 11/30 - Blade pitch-changing mechanisms
  • B64D 27/34 - All-electric aircraft

4.

FUEL SUPPLY SYSTEM FOR AN AIRCRAFT ENGINE

      
Application Number 18287745
Status Pending
Filing Date 2022-04-13
First Publication Date 2024-06-06
Owner SAFRAN HELICOPTER ENGINES (France)
Inventor
  • Benezech, Philippe Jean René Marie
  • Longin, Alexis Thomas Valentin
  • Sicaire, Pierre Anthony
  • Darrieumerlou, Gabriel

Abstract

A liquid fuel supply system for an aircraft engine includes a fuel tank, a suction duct connected to the fuel tank and located higher than the fuel tank, an electric pump, a supply pump that is mechanically driven by an accessory gear box and an outlet of the supply pump being connected to a fuel supply circuit of the engine, and an air expulsion drain. The electric pump is in communication with the suction duct independently of the supply pump, the electric pump is in communication with the air expulsion drain, and the supply pump is in communication with the suction duct independently of the electric pump.

IPC Classes  ?

  • F02C 7/236 - Fuel delivery systems comprising two or more pumps
  • F02C 7/232 - Fuel valves; Draining valves or systems
  • F02C 7/32 - Arrangement, mounting, or driving, of auxiliaries

5.

IMPROVED HYBRID TURBOPROP ENGINE FOR AIRCRAFT

      
Application Number FR2023051840
Publication Number 2024/115842
Status In Force
Filing Date 2023-11-22
Publication Date 2024-06-06
Owner SAFRAN HELICOPTER ENGINES (France)
Inventor
  • Apostin, Lucie, Stéphanie
  • Vive, Loïs, Pierre, Denis
  • Sarrat, Christian, Omer, Henri

Abstract

The invention relates to a hybrid turboprop engine (100) for an aircraft, comprising: a gas generator (12) which is supported by a generator shaft (14); a free turbine (11) which is supported by a turbine shaft (13) and rotated by a gas flow generated by the gas generator (12), the turbine shaft (13) meshing with a main rotor (60) via a transmission system (50) comprising a first overrunning clutch (51) which is oriented such that the main rotor (60) cannot drive the free turbine (11); and a reversible electric machine (30) meshing with the main rotor via the transmission system (50) in order to drive the main rotor (60) during electric or hybrid operation, the turboprop engine comprising a single oil pump (40) meshing with the transmission system (50) in order to be driven selectively by the turbine shaft (13) or by the electric machine (30) according to the operating mode.

IPC Classes  ?

  • F02C 6/20 - Adaptations of gas-turbine plants for driving vehicles
  • F02C 7/06 - Arrangement of bearings; Lubricating
  • F02C 7/32 - Arrangement, mounting, or driving, of auxiliaries
  • F02C 7/36 - Power transmission between the different shafts of the gas-turbine plant, or between the gas-turbine plant and the power user
  • F02K 5/00 - Plants including an engine, other than a gas turbine, driving a compressor or a ducted fan
  • F02C 3/10 - Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor with another turbine driving an output shaft but not driving the compressor

6.

FREE-TURBINE TURBOMACHINE COMPRISING EQUIPMENT DRIVEN BY THE FREE TURBINE

      
Application Number 18553819
Status Pending
Filing Date 2022-03-31
First Publication Date 2024-06-06
Owner SAFRAN HELICOPTER ENGINES (France)
Inventor
  • Vive, Loïs Pierre Denis
  • Drouin, Thomas
  • Bedrine, Olivier

Abstract

A turbomachine including a gas generator endowed with a first shaft, a gear box, at least one reversible electric machine coupled to the gear box, and a free turbine endowed with a second shaft and rotationally driven by a gas stream of the gas generator and at least one accessory coupled to the accessory gear box, wherein the turbomachine includes a first mechanical coupling means configured to mechanically couple said first mechanical shaft to the accessory gear box in a first configuration and to mechanically uncouple said first mechanical shaft from the accessory gear box in a second configuration, and a second mechanical coupling means configured to mechanically couple said second mechanical shaft to the accessory gear box in a first configuration and to mechanically uncouple said second mechanical shaft from the accessory gear box in a second configuration.

IPC Classes  ?

  • F01D 15/12 - Combinations with mechanical gearing
  • B64D 27/10 - Aircraft characterised by the type or position of power plant of gas-turbine type
  • F02C 7/268 - Starting drives for the rotor
  • F02C 7/32 - Arrangement, mounting, or driving, of auxiliaries

7.

METHOD FOR PROVIDING INFORMATION TO AN OPERATOR FOR MANAGING AT LEAST ONE CUMULATIVE AGEING PROCESS

      
Application Number FR2023051842
Publication Number 2024/110733
Status In Force
Filing Date 2023-11-22
Publication Date 2024-05-30
Owner SAFRAN HELICOPTER ENGINES (France)
Inventor
  • Grison, Mathieu, Louis, Antoine
  • Retoin, Vincent, Thomas
  • Clary, Estelle, Marie, Patricia
  • Toquoy, Eric, Georges, Michel

Abstract

The invention relates to a method capable of providing information to an operator, for example a pilot, or to an automated system, for example an autopilot, to assist in managing, flight after flight, at least one cumulative ageing process, for example creep, affecting at least part of a gas turbine of an aircraft of versatile use, for example a helicopter, in order to make the best use of such a turbine over the long term.

IPC Classes  ?

  • B64C 99/00 - Subject matter not provided for in other groups of this subclass
  • G06F 11/30 - Monitoring
  • G08G 5/00 - Traffic control systems for aircraft
  • G05B 19/042 - Programme control other than numerical control, i.e. in sequence controllers or logic controllers using digital processors
  • B64D 45/00 - Aircraft indicators or protectors not otherwise provided for

8.

WIRELESS DATA COLLECTION SYSTEM

      
Application Number EP2023081101
Publication Number 2024/104852
Status In Force
Filing Date 2023-11-08
Publication Date 2024-05-23
Owner
  • SAFRAN HELICOPTER ENGINES (France)
  • SAFRAN ELECTRONICS & DEFENSE (France)
Inventor
  • Lamazere, Fabien
  • Eracarret, Mathieu
  • Fanton, Nicolas

Abstract

The invention relates to an electromagnetic signal-based data collection system, comprising, on the one hand, a collector (100) provided with a first antenna (105) having a first bandwidth and, on the other hand, at least one remote electronic device (200) comprising a second antenna (205) tuned so as to exchange signals with the first antenna, characterized in that the device comprises a thermally protective block (209) in which the second antenna (205) is embedded, and in that the second antenna (205) is tuned such that the second antenna (205) and the thermally protective block (209) form a radiating assembly having a second bandwidth that coincides with the first bandwidth. The invention also relates to a vehicle (A) comprising at least one propulsion engine (M) arranged in an engine compartment (G), and at least one remote device (200) of such a system.

IPC Classes  ?

  • H01Q 1/02 - Arrangements for de-icing; Arrangements for drying-out
  • H01Q 1/28 - Adaptation for use in or on aircraft, missiles, satellites, or balloons
  • H01Q 21/28 - Combinations of substantially independent non-interacting antenna units or systems
  • H01Q 1/22 - Supports; Mounting means by structural association with other equipment or articles
  • H01Q 1/32 - Adaptation for use in or on road or rail vehicles
  • G06K 19/00 - Record carriers for use with machines and with at least a part designed to carry digital markings
  • G06K 19/077 - Constructional details, e.g. mounting of circuits in the carrier

9.

WIRELESS DATA COLLECTION SYSTEM

      
Application Number EP2023081102
Publication Number 2024/104853
Status In Force
Filing Date 2023-11-08
Publication Date 2024-05-23
Owner
  • SAFRAN HELICOPTER ENGINES (France)
  • SAFRAN ELECTRONICS & DEFENSE (France)
Inventor
  • Lamazere, Fabien
  • Eracarret, Mathieu
  • Fanton, Nicolas

Abstract

The invention relates to an electromagnetic signal-based data collection system, comprising, on the one hand, a collector (100) provided with a first antenna (105) having a predetermined bandwidth and, on the other hand, at least one remote electronic device (200) comprising a second antenna (205) having a second bandwidth that coincides with the first bandwidth for exchanging signals with the first antenna. The device comprises a thermally protective casing (207; 210) surrounding at least the second antenna (205) while defining a cavity around it, such that the second antenna radiates signals outside the protective casing substantially in the second bandwidth. The invention also relates to an aircraft equipped with such a system.

IPC Classes  ?

  • H01Q 1/00 - ANTENNAS, i.e. RADIO AERIALS - Details of, or arrangements associated with, antennas
  • H01Q 1/22 - Supports; Mounting means by structural association with other equipment or articles
  • H01Q 1/28 - Adaptation for use in or on aircraft, missiles, satellites, or balloons

10.

SYSTEM FOR PUMPING AND METERING A FLUID FOR A TURBINE ENGINE AND METHOD FOR CONTROLLING SUCH A SYSTEM

      
Application Number 18550658
Status Pending
Filing Date 2022-03-16
First Publication Date 2024-05-16
Owner SAFRAN HELICOPTER ENGINES (France)
Inventor
  • Moutaux, Antoine Pascal
  • Longin, Alexis Thomas Valentin
  • Lemay, David Bernard Martin
  • Benezech, Philippe Jean Rene Marie
  • Sicaire, Pierre Anthony

Abstract

A system for pumping and metering a fluid for a turbine engine, which system includes at least one pump for the fluid and an electronic computer configured to determine the flow rate of the fluid to be delivered to the turbine engine, the pumping and metering system being wherein it further includes a first electric motor and a second electric motor, which are each configured to drive the at least one pump, and in that the electronic computer includes a first control loop for controlling at least the first electric motor and a second control loop for controlling at least the second electric motor.

IPC Classes  ?

  • F02C 9/30 - Control of fuel supply characterised by variable fuel pump output

11.

COMBAT AIRCRAFT WITH ELECTRICAL WEAPON SYSTEM WITH OPTIMIZED POWER MANAGEMENT

      
Application Number 18552351
Status Pending
Filing Date 2022-03-22
First Publication Date 2024-05-16
Owner SAFRAN HELICOPTER ENGINES (France)
Inventor
  • Vincenzotto, Quentin
  • Mercier-Calvairac, Fabien
  • Jarin, Jean-Baptiste

Abstract

A fixed-wing combat aircraft comprising an electrical power source, a propulsion system, a low-power non-propulsion assembly comprising a flight control system, a high-power non-propulsion assembly comprising an electrical weapon system, and a management unit configured to selectively establish on command multiple operating modes comprising: a flight mode, in which the management unit distributes the electrical power supplied by the electrical power source to the propulsion system and to the low-power non-propulsion assembly, and an attack mode, in which the management unit limits the electrical power supplied by the electrical power source to the propulsion system and to the low-power non-propulsion assembly to the power required to allow the aircraft to glide, and reserves a majority of the available electrical power for the high-power non-propulsion assembly.

IPC Classes  ?

  • B64U 10/25 - Fixed-wing aircraft
  • B64U 20/83 - Electronic components structurally integrated with aircraft elements, e.g. circuit boards carrying loads
  • B64U 50/34 - In-flight charging
  • B64U 101/15 - UAVs specially adapted for particular uses or applications for conventional or electronic warfare

12.

TURBINE

      
Application Number 18278803
Status Pending
Filing Date 2022-02-23
First Publication Date 2024-05-09
Owner
  • SAFRAN AIRCRAFT ENGINES (France)
  • SAFRAN HELICOPTER ENGINES (France)
Inventor
  • Pellaton, Bertrand Guillaume, Robin
  • Zaia, Thibaud Louis

Abstract

A turbine for a turbomachine of longitudinal axis including an alternating arrangement of annular rows of movable blades and of fixed blades and a radially inner annular cavity formed radially inside the movable and fixed blades, and a supply circuit for supplying cooling air to the inner annular cavity, the downstream end of the supply circuit comprising an inner annular row of orifices and an outer annular row of orifices opening into the radially inner annular cavity. The turbine may also include means for controlling the flow rate of supply air to the orifices of the inner and outer annular rows of orifices.

IPC Classes  ?

  • F01D 9/04 - Nozzles; Nozzle boxes; Stator blades; Guide conduits forming ring or sector
  • F01D 25/24 - Casings; Casing parts, e.g. diaphragms, casing fastenings

13.

TURBOMACHINE PROVIDED WITH A MAGNETIC DRIVE PUMP

      
Application Number 18565441
Status Pending
Filing Date 2022-06-01
First Publication Date 2024-05-02
Owner SAFRAN HELICOPTER ENGINES (France)
Inventor
  • Taieb, David Simon Serge
  • Gigon, Jean-Marie Andre Robert
  • Dupeu, Franck Albert Robert

Abstract

A turbomachine including a rotary body including a motor shaft supplying mechanical power, and at least one magnetic drive pump including at least: one stator delimiting an annular inner space and including a first and a second flange, a rotor arranged in the inner space between the first and second flanges and capable of driving fluid, the rotor being able to rotate about an axis of rotation, a pair of magnets having opposite polarities coaxially arranged on the rotor with the axis of rotation, a magnet arranged on the first flange in order to co-operate with one of the magnets of the pair of magnets of the rotor, a magnetic rotator for rotating the rotor arranged on the second flange, the second flange being non-magnetic.

IPC Classes  ?

14.

DEVICE FOR SUSPENDING AN EQUIPMENT ITEM FOR A TURBOMACHINE ON A TURBOMACHINE ENGINE STRUCTURE

      
Application Number FR2023051645
Publication Number 2024/089345
Status In Force
Filing Date 2023-10-20
Publication Date 2024-05-02
Owner SAFRAN HELICOPTER ENGINES (France)
Inventor
  • Christophe, Antoine, Bernard
  • Paccini, Mathieu, Michel, Jean-Baptiste
  • Trouilhet, Vincent
  • Millet, Boris, Jean, René

Abstract

The invention relates to an assembly comprising a turbomachine engine structure (10) extending along a first axis (Z), at least one equipment item (30) and a suspension device (20) for suspending the equipment item (30) on the engine structure (10) while being offset in the direction of at least one second axis (X) perpendicular to the first axis, the suspension device (20) comprising: at least six support links (21; 22; 23; 24; 25; 26) connecting the equipment item (30) to the engine structure (10) in a statically-determinant manner; at least one safety link (27) connecting the equipment item (30) to the engine structure (10), the safety link (27) being configured to have a mechanical loading lower than a mechanical loading of each of the support links (21; 22; 23; 24; 25; 26).

IPC Classes  ?

  • F01D 25/28 - Supporting or mounting arrangements, e.g. for turbine casing

15.

TURBOMACHINE WITH RECUPERATION CYCLE EQUIPPED WITH A HEAT EXCHANGER

      
Application Number FR2023051567
Publication Number 2024/084150
Status In Force
Filing Date 2023-10-09
Publication Date 2024-04-25
Owner SAFRAN HELICOPTER ENGINES (France)
Inventor
  • Breining, Jean-Luc
  • Jousselin, Samuel Christian
  • Vive, Loïs Pierre Denis
  • Tarnowski, Laurent Pierre
  • Pons, Bernard Claude

Abstract

The present invention relates to an aircraft turbomachine (10) with a recuperation cycle, comprising: - a heat exchanger (6) comprising a first circuit (62) with an inlet (622) connected to an outlet (444) of a flow path (44) of a turbine (4), and a second circuit (64) with an inlet (642) connected to an air bleed system (20), and an air outlet (644), - at least one duct (7) for passing services (S) extending from a turbine casing (40) to a bearing housing (5), and - an air circulation device (8) comprising a first channel (82) with a first upstream end (822) connected to the system (20) and a first downstream end (824) connected to the inlet (642) and a second channel (84) having a second downstream end (844) connected to the outlet (644), and wherein the duct (7) extends radially outwards as far as the device (8).

IPC Classes  ?

  • F02C 7/08 - Heating air supply before combustion, e.g. by exhaust gases

16.

DEVICE FOR MEASURING THE ROTATIONAL SPEED OF AN AIRCRAFT PROPELLER

      
Application Number FR2023051478
Publication Number 2024/069095
Status In Force
Filing Date 2023-09-26
Publication Date 2024-04-04
Owner SAFRAN HELICOPTER ENGINES (France)
Inventor
  • Klonowski, Thomas
  • Serghine, Camel
  • Drouin, Thomas
  • Irigoyen, Jérôme

Abstract

Device (210) for measuring a rotational speed of an aircraft propeller (211), comprising: - an optical speed sensor (220); - an optical fiber (230) connected to the optical speed sensor and intended to be connected to a control unit of the aircraft; and - at least one target (251, 252) configured to follow the rotation of the propeller, the optical speed sensor being configured to detect the target.

IPC Classes  ?

  • G01P 3/481 - Devices characterised by the use of electric or magnetic means for measuring angular speed by measuring frequency of generated current or voltage of pulse signals
  • B64D 35/00 - Transmitting power from power plant to propellers or rotors; Arrangements of transmissions
  • B64C 11/50 - Phase synchronisation between multiple propellers
  • B64F 5/60 - Testing or inspecting aircraft components or systems
  • B64D 31/12 - Initiating means actuated automatically for equalising or synchronising power plants
  • B64D 45/00 - Aircraft indicators or protectors not otherwise provided for
  • B64D 27/24 - Aircraft characterised by the type or position of power plant using steam, electricity, or spring force

17.

HYBRID PROPULSION SYSTEM FOR A HELICOPTER

      
Application Number 18256855
Status Pending
Filing Date 2021-12-03
First Publication Date 2024-03-21
Owner SAFRAN HELICOPTER ENGINES (France)
Inventor
  • Thiriet, Romain Jean Gilbert
  • Mercier-Calvairac, Fabien
  • Douillard, Stéphane Albert André

Abstract

Propulsion system (2) for a helicopter (1) comprising a main engine (9), a main rotor (3), a main gearbox (4) including an output mechanically connected to the main rotor (3), a reduction gearbox (13) mechanically coupled between the main engine (9) and a first input of the main gearbox (4), and an assistance device (10). Propulsion system (2) for a helicopter (1) comprising a main engine (9), a main rotor (3), a main gearbox (4) including an output mechanically connected to the main rotor (3), a reduction gearbox (13) mechanically coupled between the main engine (9) and a first input of the main gearbox (4), and an assistance device (10). The assistance device (10) comprises a first electric machine mechanically coupled to the reduction gearbox (13) and configured to operate as an electric generator to take off energy produced by the main engine (9), and a second electric machine mechanically coupled to a second input of the main gearbox (4), the second electric machine being supplied with electrical power by the first electric machine and configured to operate as an electric motor to deliver additional mechanical power to the main gearbox (4).

IPC Classes  ?

  • B64D 27/24 - Aircraft characterised by the type or position of power plant using steam, electricity, or spring force
  • B64C 27/14 - Direct drive between power plant and rotor hub
  • B64D 31/00 - Power plant control; Arrangement thereof

18.

METHOD FOR CALIBRATING A MODEL FOR ESTIMATING A TORQUE SUPPLIED BY AN ELECTRIC MACHINE

      
Application Number FR2023051386
Publication Number 2024/056971
Status In Force
Filing Date 2023-09-12
Publication Date 2024-03-21
Owner SAFRAN HELICOPTER ENGINES (France)
Inventor
  • Lemay, David Bernard Martin
  • Frealle, Jean-Luc Charles Gilbert
  • Klonowski, Thomas

Abstract

The present application relates to a method for calibrating a model for estimating a torque supplied by an electric machine (10), which comprises the following steps: (E1) measuring an electric current in the electric machine (10) for an operating point; (E2) estimating the torque supplied by the electric machine (10) for the operating point from the measured electric current and an estimation model which associates an output torque with an input electric current; (E3) measuring a reference torque provided by the electric machine (10) for the operating point; (E4) comparing the estimated torque with the reference torque; and (E5) adjusting the estimation model so as to reduce, or even cancel, a difference between the estimated torque and the reference torque.

IPC Classes  ?

19.

PROPULSION SYSTEM FOR AN AIRCRAFT

      
Application Number 17754758
Status Pending
Filing Date 2020-10-12
First Publication Date 2024-03-14
Owner
  • SAFRAN (France)
  • SAFRAN HELICOPTER ENGINES (France)
Inventor
  • Besse, Jean-Louis Robert Guy
  • Maldonado, Ye-Bonne Karina

Abstract

The invention relates to a propulsion system (1, 1) for an aircraft, comprising a rotor (2) and a nacelle failing (3) that extends around said rotor in relation to an axis (X) and includes an upstream portion (10) forming an inlet section (BA) of the nacelle fairing (3) as well as a downstream portion (20), a downstream end (21) of which forms an outlet section (BF) of the nacelle fairing (3); and characterized in that the downstream portion (20) has a radially inner wall (20a) and a radially outer wall (20b), both of which are made of a deformable shape memory material, and in that the downstream end (21) includes pneumatic or hydraulic actuators (23, 23′) extending in different consecutive angular sectors about said axis (X), each actuator being independently actuatable and being configured to deform, in a direction that extends radially in relation to said axis (X) and is centered angularly in relation to its angular sector, under the effect of a predetermined control pressure.

IPC Classes  ?

  • F02K 1/00 - Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
  • B64D 29/00 - Power-plant nacelles, fairings, or cowlings

20.

ROTOR FOR A TURBOMACHINE CENTRIFUGAL BREATHER

      
Application Number 18261094
Status Pending
Filing Date 2022-02-09
First Publication Date 2024-03-14
Owner SAFRAN HELICOPTER ENGINES (France)
Inventor
  • Marsaudon, Mathieu Jean-Baptiste
  • Berteaux, Olivier Philippe David

Abstract

A rotor for a centrifugal breather for an air/oil mixture of a turbomachine, this rotor including a hollow shaft extending along an axis, a pinion for rotating the hollow shaft, this pinion extending around the axis and being formed of a single part and in a first material with at least one first portion of the hollow shaft, and an annular structure extending around the axis and constrained to rotate with the shaft, this structure being produced in a second material, different from the first material, wherein the structure is made integral with the shaft by additive manufacturing of this structure directly on at least one annular surface of the pinion which forms at least one annular support surface for this additive manufacturing.

IPC Classes  ?

  • F01D 25/18 - Lubricating arrangements
  • F01M 13/04 - Crankcase ventilating or breathing having means for purifying air before leaving crankcase, e.g. removing oil

21.

EURA

      
Application Number 018994753
Status Pending
Filing Date 2024-03-05
Owner
  • SAFRAN HELICOPTER ENGINES (France)
  • MTU Aero Engines GmbH (Germany)
NICE Classes  ?
  • 07 - Machines and machine tools
  • 09 - Scientific and electric apparatus and instruments
  • 35 - Advertising and business services
  • 37 - Construction and mining; installation and repair services
  • 42 - Scientific, technological and industrial services, research and design

Goods & Services

Generators for aircraft, Compressors; Transmission and propulsion couplings and components (except for land vehicles); Propulsive and non-propulsive power systems machines, For use with the following goods: Aircraft and components thereof included in this class, including turbines, motors and engines, propellers, engine cars, thrust reversers; Auxiliary power units for air vehicles (machines); Lubrication systems for engines and turbines of air vehicles (machines); Test benches for engines, turbines and other propellers (machines) for aircraft. Electric and electronic apparatus and instruments, namely generators and/or starters for static or mobile installations for aircraft; Electric, electronic and magnetic pressure, speed, motion, temperature, position and vibration sensors; Electronic systems, apparatus and equipment, whether on-board or not, for the acquisition and processing of parameters and data; Electric and electronic hardware and equipment for maintaining and controlling generators, starters and integrated assemblies for the generation of propulsive and non-propulsive power. Services in connection with the sale of the following goods: Propulsive and non-propulsive power systems (machines) for aircraft; Administrative and commercial management of parts and spare parts for users of engines, systems, equipment and parts for aircraft; Business organisation consultancy, in relation to the following fields: Aircraft propulsion systems, turbines. Repair, overhaul, Maintenance and Maintenance, In connection with the following goods: Propulsive and non-propulsive power systems (machines) for aircraft and components therefor, including turbines, motors and engines, propellers, engine cars, thrust inverters; Consultancy relating to the identification and selection of tools for the repair, servicing, upkeep, standardisation and maintenance of systems, equipment and parts for aeronautical vehicles. Technical, scientific and industrial research; Engineering services; Research and development (engineering) in the field of aeronautics; Analysis of technical data; Engineering in relation to evaluation, assessment and research in connection with technologies used in aeronautical vehicle systems, equipment and parts; Testing of machines and materials; Computer software design and computer programming; Analysis and surveying of equipment and parts for aircraft; Analysis, surveying and processing of the acquisition of data recorded during the operation of engines, systems, equipment and parts for aircraft; Conducting technical project studies, In connection with the following goods: Air vehicles and components therefor, including motors and engines, engine cars, reactors, propellers or reverse thrusters, air vehicles.

22.

IGNITION METHOD AND DEVICE

      
Application Number 18260880
Status Pending
Filing Date 2021-12-20
First Publication Date 2024-02-15
Owner SAFRAN HELICOPTER ENGINES (France)
Inventor
  • Bondivenne, Eric Michel
  • Poumarede, Vincent

Abstract

A method for igniting a continuous combustion engine including an electronic engine control member, a high energy box, a spark plug ignition circuit and a fuel solenoid valve, cooperating with a starter motor, the method being implemented by the electronic engine control member and including precharging the high energy box before an engine starting procedure, activated on an engine starting command, the precharging being controlled by switching on the electronic engine control member, or by putting the engine in idle mode.

IPC Classes  ?

23.

METHOD FOR MANAGING THE OUTPUT OF A SPECIFIC-CONSUMPTION MODE OF AN AIRCRAFT TURBINE ENGINE

      
Application Number FR2023051254
Publication Number 2024/033593
Status In Force
Filing Date 2023-08-08
Publication Date 2024-02-15
Owner SAFRAN HELICOPTER ENGINES (France)
Inventor
  • Humbert, Sophie
  • Bedrine, Olivier
  • Carles, Sébastien Alexis Matthieu

Abstract

This method for managing the output of a specific-consumption mode of an aircraft comprises a step of identifying a need to reactivate a turbine engine in the nominal mode of said turbine engine, and a step of: - normal reactivation of the turbine engine in the nominal mode for the turbine engine for a first duration when a first condition (C1) is met (step 10); - accelerated reactivation of the turbine engine in the nominal mode for the turbine engine for a second duration when a second condition (C2) is met (step 12); - rapid reactivation of the turbine engine in the nominal mode of the turbine engine for a third duration when a third condition (C3) is met (step 14), the first duration being longer than the second duration, and the second duration being longer than the third duration.

IPC Classes  ?

  • F01D 19/00 - Starting of machines or engines; Regulating, controlling, or safety means in connection therewith

24.

METHOD FOR ASSISTING WITH PROPULSION BY DETECTING A FAILURE OF A TURBOSHAFT ENGINE OF AN AIRCRAFT

      
Application Number FR2023051256
Publication Number 2024/033594
Status In Force
Filing Date 2023-08-08
Publication Date 2024-02-15
Owner SAFRAN HELICOPTER ENGINES (France)
Inventor
  • Carles, Sébastien Alexis Matthieu
  • Marin, Jean-Philippe Jacques
  • Humbert, Sophie

Abstract

The invention relates to a method for assisting with propulsion by detecting a failure of a turboshaft engine of an aircraft operating in a nominal mode, the aircraft comprising a deactivated assistance motor, which method comprises a step (2) of comparing operating parameters of the turboshaft engine with the equivalent parameters of a model representative of a healthy turboshaft engine, a step (4) of detecting a failure of the turboshaft engine by detecting an anomaly in at least one operating parameter of the turboshaft engine, a step (6) of selecting an activation mode for the assistance motor on the basis of the operating parameters of the turboshaft engine and/or of flight parameters of the aircraft, and a step (8) of activating the assistance motor with the selected activation mode.

IPC Classes  ?

  • F01D 13/00 - Combinations of two or more machines or engines
  • B64C 27/12 - Rotor drives
  • F01D 19/00 - Starting of machines or engines; Regulating, controlling, or safety means in connection therewith

25.

Torque transmission and measurement assembly for a turbomachine

      
Application Number 18270287
Status Pending
Filing Date 2021-12-29
First Publication Date 2024-02-15
Owner SAFRAN HELICOPTER ENGINES (France)
Inventor
  • Fulleringer, Benjamin Nicolas
  • Lanquetin, Rémi Joseph
  • Nifenecker, Arnaud Georges

Abstract

An assembly for measuring a torque transmitted between a first member and a second member of a turbomachine includes a pinion having a first annular portion and a second annular portion joining together at a connecting portion carrying a gearing of the pinion, said first and second annular portions extending axially in opposite directions, from the connecting portion. The pinion also includes an axial power shaft with a first area coupled to the first annular portion, and a second area for coupling to the second member, and a device for measuring the torsion between the first and second areas. The device includes a first phonic wheel on the power shaft, a second phonic wheel equipping the second annular portion of the pinion and axially aligned with the first phonic wheel, and an acquisition means axially aligned with and opposite to the first phonic wheel and the second phonic wheel and outputting a signal representative of an angular variation.

IPC Classes  ?

  • G01L 3/08 - Rotary-transmission dynamometers wherein the torque-transmitting element comprises a torsionally-flexible shaft involving optical means for indicating

26.

RECOVERED-CYCLE AIRCRAFT TURBINE ENGINE

      
Application Number FR2023051234
Publication Number 2024/033588
Status In Force
Filing Date 2023-08-03
Publication Date 2024-02-15
Owner SAFRAN HELICOPTER ENGINES (France)
Inventor
  • Auduberteau, Alexandre
  • Scuiller, Lionel
  • Puerto, Alphonse

Abstract

The invention relates to an aircraft turbine engine (10) having: - a compressor (14), - an annular combustion chamber (24), - a system (32) for diffusing and straightening an air stream exiting the compressor in order to supply the combustion chamber, and - a heat exchanger (38), this heat exchanger having: + a first circuit (38a) supplied with exhaust gas from the turbine engine, and + a second circuit (38b) comprising an inlet (38ba) connected by a first scroll (40a) to an outlet (34b) of the diffuser (34), and an outlet (38bb) connected by a second scroll (40b) to an inlet (36a) of the straightener (36), the scrolls (40a, 40b) comprising connecting arms (82, 84) that rigidly connect the annular portions (86, 88, 94) of the scrolls which are secured or connected to the diffuser (34) and to the straightener (36), respectively. Figure for the abstract: Figure 5

IPC Classes  ?

  • F02C 3/09 - Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising at least one radial stage of the centripetal type
  • F01D 9/02 - Nozzles; Nozzle boxes; Stator blades; Guide conduits
  • F02C 7/08 - Heating air supply before combustion, e.g. by exhaust gases
  • F04D 29/44 - Fluid-guiding means, e.g. diffusers
  • F04D 29/58 - Cooling; Heating; Diminishing heat transfer

27.

DOUBLE WALL FOR AIRCRAFT GAS TURBINE COMBUSTION CHAMBER AND METHOD OF PRODUCING SAME

      
Application Number 18258356
Status Pending
Filing Date 2021-12-20
First Publication Date 2024-02-08
Owner SAFRAN HELICOPTER ENGINES (France)
Inventor
  • Gresy, Thomas Sébastien Alexandre
  • Autret, Jean-Paul Didier
  • Savary, Nicolas Roland Guy

Abstract

A double wall for an aircraft gas turbine combustion chamber comprising an internal wall which is configured to be in contact with the combustion reaction, and an external wall which is at a distance from the internal wall, comprising a plurality of openings so as to allow the circulation of cooling air streams outside the external wall, which cool the internal wall. The internal wall being free of perforations prevent any circulation of a cooling air stream towards the centre of the combustion chamber. The the internal wall comprises a plurality of members projecting towards the external wall, each projecting member comprising a foot portion and a cylindrical head portion with a circular cross-section, the head portion extending into an opening with a circular cross-section so as to define a calibrated cross-sectional area between the projecting member and the opening, through which area a cooling air stream can flow.

IPC Classes  ?

  • F23R 3/00 - Continuous combustion chambers using liquid or gaseous fuel

28.

TURBOPROP CAPABLE OF PROVIDING AN EMERGENCY WIND TURBINE FUNCTION AND METHOD OF IMPLEMENTATION

      
Application Number FR2023051224
Publication Number 2024/028553
Status In Force
Filing Date 2023-08-01
Publication Date 2024-02-08
Owner SAFRAN HELICOPTER ENGINES (France)
Inventor
  • Apostin, Lucie Stéphanie
  • Chartrain, Didier Claude
  • Presse, Jean-Michel

Abstract

The invention relates to a turboprop (10) comprising: - a turbine (12) mechanically connected to an input (21) of a reducer (20); - a tail shaft (30) bearing a variable-pitch propeller (31); - a rotary electric machine (46); and - an electric oil pump (40) configured to supply a hydraulic circuit (33) for adjusting the pitch of the propeller (31), wherein the electric oil pump (40) is configured to supply a lubrication circuit (53) for lubricating the bearings (25) of the reducer (20).

IPC Classes  ?

  • B64C 11/38 - Blade pitch-changing mechanisms fluid, e.g. hydraulic
  • F01D 15/10 - Adaptations for driving, or combinations with, electric generators
  • F01D 17/26 - Devices dealing with sensing elements or final actuators or transmitting means between them, e.g. power-assisted the operation or power assistance being predominantly non-mechanical fluid, e.g. hydraulic
  • F01D 21/14 - Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to other specific conditions
  • F01D 25/18 - Lubricating arrangements
  • F02C 6/20 - Adaptations of gas-turbine plants for driving vehicles
  • F02C 7/32 - Arrangement, mounting, or driving, of auxiliaries
  • B64C 11/32 - Blade pitch-changing mechanisms mechanical
  • B64D 35/00 - Transmitting power from power plant to propellers or rotors; Arrangements of transmissions
  • F02C 9/58 - Control of fuel supply conjointly with another control of the plant with power transmission control with control of a variable-pitch propeller

29.

MONITORING OF AN AIRCRAFT PROPULSION SYSTEM

      
Application Number FR2023051196
Publication Number 2024/023461
Status In Force
Filing Date 2023-07-27
Publication Date 2024-02-01
Owner SAFRAN HELICOPTER ENGINES (France)
Inventor
  • Lemay, David Bernard Martin
  • Marin, Jean-Philippe Jacques
  • Thiriet, Romain Jean Gilbert

Abstract

The invention relates to a method for monitoring a propulsion system (102) of an aircraft (100), which comprises: - calculating, for each damage counter (FC, EF), a maximum incrementation rate (dC_FC_max, dC_EF_max) of the counter (FC, EF) so that the counter (FC, EF) remains below a predefined threshold (C_FC_max, C_EF_max) throughout a target service life (DDV_cible); - calculating, on the basis of one or more thresholds (NGmax FC, NGmax EF, T4xmax_EF) of at least one parameter (NG, T4x), at least one limit (PEinf, PEsup) of an operating variable of the turboshaft engine (TM) which must not be exceeded so that the incrementation rate (dC_FC, dC_EF) of the counter (FC, EF) remains below the maximum incrementation rate (dC_FC_max, dC_EF_max); and - transmitting a current value and the limit (PEinf, PEsup) of the operating variable to a display device (AF) of the aircraft (100).

IPC Classes  ?

  • F01D 21/00 - Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
  • G01M 15/05 - Testing internal-combustion engines by combined monitoring of two or more different engine parameters
  • G01M 15/14 - Testing gas-turbine engines or jet-propulsion engines
  • G05B 23/02 - Electric testing or monitoring

30.

IMPROVED PROPULSION ASSEMBLY FOR MULTI-ENGINE HYBRID AIRCRAFT

      
Application Number FR2023050945
Publication Number 2024/023413
Status In Force
Filing Date 2023-06-22
Publication Date 2024-02-01
Owner SAFRAN HELICOPTER ENGINES (France)
Inventor
  • Thiriet, Romain, Jean, Gilbert
  • Bedrine, Olivier

Abstract

Disclosed is a propulsion assembly (100) for a hybrid aircraft, comprising a first engine (1) and a second engine (2) each having a gas generator (12, 22) and a free turbine (11, 21), a main rotor (62) coupled to the free turbine (11, 21), the engines (1, 2) each comprising a first electric machine (30, 40) and a second electric machine (32, 42) that is less powerful than the first electric machine, one of the electric machines being coupled to the gas generator (12, 22) to rotate the gas generator during a starting phase, and being coupled to the free turbine (11, 21) after the starting phase to generate electric energy, the other of the electric machines being coupled to the gas generator (12, 22) only, at least one of the first and second electric machines of the first engine (1) and/or the second engine (2) being able to transmit electric energy to the other electric machine.

IPC Classes  ?

  • F02C 3/10 - Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor with another turbine driving an output shaft but not driving the compressor
  • F02C 6/02 - Plural gas-turbine plants having a common power output
  • F02C 6/20 - Adaptations of gas-turbine plants for driving vehicles
  • F02C 7/268 - Starting drives for the rotor
  • F02C 7/26 - Starting; Ignition
  • F02C 3/113 - Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor with two or more rotors connected by power transmission with variable power transmission between rotors

31.

IMPROVED PROPULSION ASSEMBLY FOR MULTI-ENGINE HYBRID AIRCRAFT

      
Application Number FR2023051166
Publication Number 2024/023445
Status In Force
Filing Date 2023-07-26
Publication Date 2024-02-01
Owner SAFRAN HELICOPTER ENGINES (France)
Inventor
  • Thiriet, Romain, Jean, Gilbert
  • Bedrine, Olivier

Abstract

Disclosed is a propulsion assembly (100) for a hybrid aircraft, comprising a first engine (1) and a second engine (2) each having a gas generator (12, 22) and a free turbine (11, 21), a main rotor (62) coupled to the free turbines (11, 21) of the first and second engines (1, 2), the first engine (1) comprising a first electric machine (30) and a second electric machine (32) that is less powerful than the first electric machine (30), one of the first and second electric machines (30, 32) being able to be coupled to the gas generator (12) and to rotate the gas generator during a starting phase of the engine, and also being able to be coupled to the free turbine (11) in order to generated electric energy after the starting phase, the other of the first and second electric machines being coupled to the gas generator (12) only.

IPC Classes  ?

  • F02C 3/10 - Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor with another turbine driving an output shaft but not driving the compressor
  • F02C 6/02 - Plural gas-turbine plants having a common power output
  • F02C 6/20 - Adaptations of gas-turbine plants for driving vehicles
  • F02C 7/268 - Starting drives for the rotor
  • F02C 7/26 - Starting; Ignition
  • F02C 3/113 - Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor with two or more rotors connected by power transmission with variable power transmission between rotors

32.

MONITORING A PROPULSION SYSTEM OF AN AIRCRAFT

      
Application Number FR2023051197
Publication Number 2024/023462
Status In Force
Filing Date 2023-07-27
Publication Date 2024-02-01
Owner SAFRAN HELICOPTER ENGINES (France)
Inventor
  • Lemay, David Bernard Martin
  • Marin, Jean-Philippe Jacques
  • Thiriet, Romain Jean Gilbert

Abstract

The invention relates to a method for monitoring a propulsion system (102) of an aircraft (100), comprising: - computing a margin of a parameter (NG, T4x) of a thermal chain (TH), this margin being taken as margin (PMD1, PMT1) of the thermal chain (TH); - computing a margin of a parameter (IBAT) of an electrical chain (ELEC), at least part of this margin being taken as margin of the electrical chain (ELEC); - adding together the margin (PMD1, PMT1) of the thermal chain (TH) and the margin of the electrical chain (ELEC) so as to obtain a total margin (ePMD) of the propulsion system (102); and - transmitting the total margin (ePMD) to a display device (AF) in the aircraft (100) so that the display device (AF) displays the total margin (ePMD).

IPC Classes  ?

  • B64D 27/24 - Aircraft characterised by the type or position of power plant using steam, electricity, or spring force
  • B64D 35/08 - Transmitting power from power plant to propellers or rotors; Arrangements of transmissions characterised by the transmission being driven by a plurality of power plants
  • B64D 45/00 - Aircraft indicators or protectors not otherwise provided for

33.

HYBRID PROPULSION SYSTEM FOR AN AIRCRAFT

      
Application Number FR2023051064
Publication Number 2024/018137
Status In Force
Filing Date 2023-07-10
Publication Date 2024-01-25
Owner SAFRAN HELICOPTER ENGINES (France)
Inventor
  • Thiriet, Romain Jean Gilbert
  • Serghine, Camel
  • Drouin, Thomas

Abstract

The invention relates to a hybrid propulsion system (2) comprising: a turbine engine (3) comprising a high-pressure spool (4) and a low-pressure spool (5), the low-pressure spool (5) comprising reduction gear (11), the reduction gear (11) forming part of a transmission gearbox (12) which is positioned axially at a front end (13) of the propulsion system (2); - first and second electric machines (14, 15) mechanically and respectively connected to the high-pressure and low-pressure spools (4, 5), the electric machines (14, 15) being configured to operate in modes referred to as motor and generator, the first and second electric machines (14, 15) being fixed to the transmission gearbox (12); - a control system (16) which is configured to allow the transfer of power between the high-pressure and low-pressure spools (4, 5) via the first and second electric machines (14, 15).

IPC Classes  ?

  • F02C 7/275 - Mechanical drives
  • B64C 27/12 - Rotor drives
  • F02C 7/32 - Arrangement, mounting, or driving, of auxiliaries
  • F02C 3/107 - Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor with two or more rotors connected by power transmission
  • F02C 7/36 - Power transmission between the different shafts of the gas-turbine plant, or between the gas-turbine plant and the power user
  • F01D 15/10 - Adaptations for driving, or combinations with, electric generators

34.

METHOD FOR STOPPING A GAS TURBINE ENGINE OF A TURBOGENERATOR FOR AIRCRAFT

      
Application Number 18265021
Status Pending
Filing Date 2021-12-01
First Publication Date 2024-01-04
Owner
  • SAFRAN (France)
  • SAFRAN HELICOPTER ENGINES (France)
  • SAFRAN POWER UNITS (France)
Inventor
  • Mercier-Calvairac, Fabien
  • Parmentier, Nicolas Claude
  • Real, Denis Antoine Julien

Abstract

This method for stopping at least one aircraft turbogenerator (1) comprises: —controlling the stopping (E1) of the turbogenerator (1); —passing from the nominal operating speed (Nref) of the power shaft (3, 12) to a first operating speed (N1) lower than the nominal speed (Nref), for a first predetermined duration (t2); —controlling the extinction of the combustion chamber (6) of the gas turbine (2); —maintaining the rotation of the gas turbine at a second speed (N2) for a second predetermined duration (t3), the power shaft (3, 12) being at a second speed (N2) lower than the first operating speed (N1) and, —controlling the stopping of the reversible electric machine (7) in order to no longer drive the power shaft (3, 12), in order to cause a progressive stopping (E9, E10) of the rotation of the gas turbine (2).

IPC Classes  ?

  • F01D 15/10 - Adaptations for driving, or combinations with, electric generators
  • F01D 21/00 - Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for

35.

HYBRID PROPULSION TURBOMACHINE AND AIRCRAFT COMPRISING SUCH A TURBOMACHINE

      
Application Number 18253081
Status Pending
Filing Date 2021-11-05
First Publication Date 2023-12-28
Owner SAFRAN HELICOPTER ENGINES (France)
Inventor
  • Klonowski, Thomas
  • Apostin, Lucie Stéphanie

Abstract

A turbomachine includes a propeller, a propeller shaft carrying the propeller, a rotating electric machine, having at least a first configuration in which it is mechanically coupled to the propeller shaft, and a motor oil pump supplying a lubricating circuit of the turbomachine. The rotating electric machine in the first configuration is mechanically coupled to the motor oil pump in such a way that the rotating electric machine additionally drives the motor oil pump when it is supplied with current. Also disclosed is an aircraft including such a turbomachine.

IPC Classes  ?

  • F02C 6/20 - Adaptations of gas-turbine plants for driving vehicles
  • F02C 7/32 - Arrangement, mounting, or driving, of auxiliaries
  • F02C 7/06 - Arrangement of bearings; Lubricating

36.

Device for controlling an airflow guiding system, in particular in an aircraft turbine engine

      
Application Number 18034988
Grant Number 11982192
Status In Force
Filing Date 2021-11-10
First Publication Date 2023-12-28
Grant Date 2024-05-14
Owner SAFRAN HELICOPTER ENGINES (France)
Inventor
  • Imbourg, Frédéric Anthony Alain
  • Chabanne, Pierre
  • Javoy, Thibaut Maxime

Abstract

a) at a safe pitch angle between the first angle and the second angle.

IPC Classes  ?

  • F01D 17/16 - Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
  • F04D 29/56 - Fluid-guiding means, e.g. diffusers adjustable

37.

METHOD FOR DETERMINING AN EFFICIENCY FAULT OF AN AIRCRAFT TURBOSHAFT ENGINE MODULE

      
Application Number 18251340
Status Pending
Filing Date 2021-10-28
First Publication Date 2023-12-28
Owner
  • SAFRAN (France)
  • SAFRAN HELICOPTER ENGINES (France)
Inventor
  • Razakarivony, Sébastien Philippe
  • Favre, Christophe
  • Joseph, Julien
  • Lamouroux, Jean

Abstract

A method for determining an efficiency fault of at least one module of a turboshaft engine of an aircraft. The method comprising a step of determining an estimated real mapping, a step of determining real indicators from the estimated real mapping, a step of determining a plurality of simulated mappings from a simulation of a theoretical model of the turboshaft engine for different efficiency configurations, a step of determining simulated indicators for each simulated mapping, a step of training a mathematical model by coupling the simulated indicators with efficiency configurations, and a step of applying said mathematical model to the real indicators so as to deduce therefrom a real efficiency configuration.

IPC Classes  ?

  • B64F 5/60 - Testing or inspecting aircraft components or systems
  • F02C 7/00 - Features, component parts, details or accessories, not provided for in, or of interest apart from, groups ; Air intakes for jet-propulsion plants

38.

ELECTRIC MACHINE FOR AN AIRCRAFT, COMPRISING AT LEAST ONE MEMBER FOR PROTECTING AGAINST A SHORT CIRCUIT BETWEEN TWO STATOR PHASES, AND PROTECTION METHOD

      
Application Number EP2023064355
Publication Number 2023/241902
Status In Force
Filing Date 2023-05-30
Publication Date 2023-12-21
Owner SAFRAN HELICOPTER ENGINES (France)
Inventor
  • Lemay, David, Bernard, Martin
  • Klonowski, Thomas

Abstract

The invention relates to an electric machine for an aircraft, comprising a stator (1) comprising at least three phases (10) each comprising a winding (12), a control branch (11) and a neutral branch (13), the neutral branches (13) being connected together at a neutral point (14), the electric machine (3) comprising at least one protection member (5) mounted on the neutral branch (13) of at least one phase (10), each protection member (5) comprising: an inactive state (P1), in which the protection member (5) allows the circulation of the electric current in each phase (10) on which the protection member (5) is mounted, and a protection state (P2), in which the protection member (5) interrupts the circulation of the electric current in each phase (10) on which the protection member (5) is mounted, so as to protect the electric machine in the event of a short circuit (CC).

IPC Classes  ?

  • H02H 3/08 - Emergency protective circuit arrangements for automatic disconnection directly responsive to an undesired change from normal electric working condition, with or without subsequent reconnection responsive to excess current
  • H02H 7/08 - Emergency protective circuit arrangements specially adapted for specific types of electric machines or apparatus or for sectionalised protection of cable or line systems, and effecting automatic switching in the event of an undesired change from norm for dynamo-electric motors

39.

METHOD FOR DETERMINING AT LEAST ONE POWER LIMIT OF A HYBRID DRIVE TRAIN FOR A TRANSPORT VEHICLE, IN PARTICULAR AN AIRCRAFT

      
Application Number 18246984
Status Pending
Filing Date 2021-11-08
First Publication Date 2023-12-14
Owner SAFRAN HELICOPTER ENGINES (France)
Inventor
  • Lemay, David Bernard Martin
  • Marin, Jean-Philippe Jacques

Abstract

A method for determining at least one minimum power margin of a hybrid drive train for a transport vehicle, each drive element being associated with at least one power source and at least one power consumer. The method including a step of acquiring measurements of power parameters, a step of comparing each measurement with at least one limitation threshold, so as to deduce therefrom at least one gross margin, a step of converting the gross margins into refined margins expressed according to the same common magnitude, a step of transposing into standardised margins at least at one reference point, a step of determining a source power margin and a consumer power margin at said reference point and a step of determining the minimum power margin by selecting the lowest power margin.

IPC Classes  ?

  • B64D 43/00 - Arrangements or adaptations of instruments
  • B64D 27/24 - Aircraft characterised by the type or position of power plant using steam, electricity, or spring force
  • B64D 35/08 - Transmitting power from power plant to propellers or rotors; Arrangements of transmissions characterised by the transmission being driven by a plurality of power plants

40.

IMPROVED PROPULSION ASSEMBLY FOR A MULTI-ENGINE AIRCRAFT

      
Application Number FR2023050748
Publication Number 2023/233097
Status In Force
Filing Date 2023-05-29
Publication Date 2023-12-07
Owner SAFRAN HELICOPTER ENGINES (France)
Inventor
  • Vincenzotto, Quentin
  • Bedrine, Olivier

Abstract

Propulsion assembly (100) for an aircraft, in particular a multi-engine helicopter, comprising at least a first engine (1) and a second engine (2) that are configured to operate in at least one standby mode, a primary air-circulation device (30) configured to bleed air from the first engine (1) via a first bleed channel (310) and/or from the second engine (2) via a second bleed channel (320) in order to convey it to equipment of the propulsion assembly (100), and a secondary air-circulation device (40) configured, when one of the first or the second engine (1, 2) operates in standby mode, to bleed air from the other of the first or the second engine (1, 2) not operating in standby mode and to convey it to the one of the first or the second engine (1, 2) operating in standby mode.

IPC Classes  ?

  • B64D 15/04 - Hot gas application
  • F02C 9/18 - Control of working fluid flow by bleeding, by-passing or acting on variable working fluid interconnections between turbines or compressors or their stages

41.

METHOD FOR ASSEMBLING METAL PARTS OF DIFFERENT SIZES AND CENTRIFUGAL DIFFUSER PRODUCED BY THIS METHOD

      
Application Number FR2023050755
Publication Number 2023/233103
Status In Force
Filing Date 2023-05-30
Publication Date 2023-12-07
Owner SAFRAN HELICOPTER ENGINES (France)
Inventor
  • Larrouy, Thibaut
  • Ezcurra, Daniel
  • Scuiller, Lionel

Abstract

The invention relates to a method for assembling a first metal part (21) to a second metal part (22), the first and second metal parts having different sizes, the method comprising the following operations: - a) producing (110) a slot (23) in a surface of the first metal part (22); - b) positioning (120) the second metal part (22) in line with the slot (23) of the first metal part; and - c) welding (130) the second metal part (22) to the first metal part (21) through the slot (23) using a high-energy welding beam, the slot guiding the welding beam. The invention also relates to a centrifugal diffuser for turbomachinery comprising a metal cover (21) and a plurality of metal blades (22), each blade (22) being assembled with the cover (21) by means of the method hereinbefore.

IPC Classes  ?

  • F04D 29/44 - Fluid-guiding means, e.g. diffusers
  • F04D 29/60 - Mounting; Assembling; Disassembling
  • B23P 15/00 - Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
  • F04D 29/62 - Mounting; Assembling; Disassembling of radial or helico-centrifugal pumps
  • F04D 29/02 - Selection of particular materials
  • B23K 15/00 - Electron-beam welding or cutting
  • B23K 26/00 - Working by laser beam, e.g. welding, cutting or boring

42.

TURBOMACHINE BLADE, TURBOMACHINE AND METHOD FOR MANUFACTURING THE BLADE

      
Application Number FR2023050747
Publication Number 2023/233096
Status In Force
Filing Date 2023-05-29
Publication Date 2023-12-07
Owner SAFRAN HELICOPTER ENGINES (France)
Inventor
  • Laberny, Damien
  • Vive, Loïs, Pierre, Denis
  • Montpellaz, Alexandre, Hervé, René
  • Iparaguirre, Fabrice

Abstract

The invention relates to a turbomachine blade (1) comprising: an external enclosure (10) comprising a pressure-side wall (11) and a suction-side wall (12) delimiting an interior volume therebetween; an insert (30) arranged in the interior volume so as to form an air passage (40) between the insert (30) and the external enclosure (10); and at least one breakable joining part (20) connected to the insert (30) on one side and to the external enclosure (10) on the other side; wherein at least one of the mechanical breaking strength of the breakable joining part (20), the mechanical breaking strength between the breakable joining part (20) and the external enclosure (10) and the mechanical breaking strength between the breakable joining part (20) and the insert (30) is lower than the mechanical breaking strength of the external enclosure (10) and the mechanical breaking strength of the insert (30).

IPC Classes  ?

  • F01D 5/18 - Hollow blades; Heating, heat-insulating, or cooling means on blades
  • F01D 9/06 - Fluid supply conduits to nozzles or the like

43.

METHOD FOR DIMENSIONALLY INSPECTING A COMPONENT DURING ADDITIVE MANUFACTURING THEREOF

      
Application Number FR2023050722
Publication Number 2023/227843
Status In Force
Filing Date 2023-05-19
Publication Date 2023-11-30
Owner SAFRAN HELICOPTER ENGINES (France)
Inventor
  • Danis, Yann Bernard
  • Carballo, Nicolas

Abstract

One aspect of the invention relates to a method for dimensionally inspecting at least one component manufactured by means of an additive manufacturing machine, the step of additive manufacturing being carried out by successive depositions of a powder bed and by fusing the powder bed after each deposition, the method comprising the steps of: - acquiring an image of the component being manufactured after at least one step of depositing and fusing the powder bed; - comparing the image with an image of a reference template; - verifying the dimensional conformity of the component on the basis of the comparison.

IPC Classes  ?

44.

SYNCHRONOUS ELECTRIC MACHINE FOR AIRCRAFT, ASSOCIATED PROPULSION DEVICE, TURBOSHAFT ENGINE AND METHOD

      
Application Number EP2023062669
Publication Number 2023/222523
Status In Force
Filing Date 2023-05-11
Publication Date 2023-11-23
Owner SAFRAN HELICOPTER ENGINES (France)
Inventor
  • Klonowski, Thomas
  • Humbert, Sophie
  • Lemay, David
  • Figielski, Alexandre Edouard Emile

Abstract

The invention relates to a synchronous electric machine (10) for aircraft, which comprises a stator (13) and a wound rotor (38) inserted into the stator, the stator comprising two sets of stator coils (47, 49) intended to be connected to different power converters, and the wound rotor comprising a rotor shaft (11) and two rotor coils (39, 40) each intended to be supplied with a different supply current. The two sets of stator coils are arranged in the stator in such a way that when a first set of stator coils (47) fails, the second set of stator coils (49) cooperates with at least the second rotor coil (40) supplied with the associated supply current in order to generate a mechanical torque on the rotor shaft, and so that the power converter connected to the first set of stator coils does not deliver any electrical power.

IPC Classes  ?

  • H02K 11/33 - Drive circuits, e.g. power electronics
  • H02K 16/00 - Machines with more than one rotor or stator
  • H02P 25/022 - Synchronous motors
  • H02K 19/12 - Synchronous motors for multi-phase current characterised by the arrangement of exciting windings, e.g. for self-excitation, compounding or pole-changing
  • H02K 19/26 - Synchronous generators characterised by the arrangement of exciting windings

45.

FREE TURBINE TURBOMACHINE COMPRISING EQUIPMENT DRIVEN BY THE FREE TURBINE

      
Application Number 18251025
Status Pending
Filing Date 2021-10-21
First Publication Date 2023-11-16
Owner SAFRAN HELICOPTER ENGINES (France)
Inventor
  • Vive, Loïs Pierre Denis
  • Drouin, Thomas
  • Bedrine, Olivier

Abstract

Disclosed is a turbomachine, comprising a gas generator (13) equipped with a first shaft (18), at least one reversible electrical machine (11), a free turbine (12) provided with a second shaft (17) and caused to rotate by a gas flow generated by the gas generator (13), an accessory gear box (14) and at least one accessory (15, 16). Disclosed is a turbomachine, comprising a gas generator (13) equipped with a first shaft (18), at least one reversible electrical machine (11), a free turbine (12) provided with a second shaft (17) and caused to rotate by a gas flow generated by the gas generator (13), an accessory gear box (14) and at least one accessory (15, 16). Said at least one electrical machine (11) is mechanically coupled to said second mechanical shaft (17) via the accessory gear box (14) during all phases of operation of the turbomachine (10), the accessory gear box (14) is coupled to the at least one accessory (15, 16) and the turbomachine (10) further comprises a single mechanical coupling means (20) for mechanically coupling said first mechanical shaft (18) to the accessory gear box (14) in a first configuration and mechanically uncoupling said first mechanical shaft (18) from the accessory gear box (14) in a second configuration.

IPC Classes  ?

  • F02C 7/275 - Mechanical drives
  • F01D 15/10 - Adaptations for driving, or combinations with, electric generators
  • F02C 7/32 - Arrangement, mounting, or driving, of auxiliaries

46.

HYBRID ELECTRICAL ARCHITECTURE FOR AN AIRCRAFT

      
Application Number FR2023000070
Publication Number 2023/214128
Status In Force
Filing Date 2023-04-28
Publication Date 2023-11-09
Owner SAFRAN HELICOPTER ENGINES (France)
Inventor
  • Thiriet, Romain Jean Gilbert
  • Lemay, David Bernard Martin
  • Humbert, Sophie

Abstract

The invention relates to a hybrid electrical architecture (101) for an aircraft (103) which comprises a turbomachine (107) and a reduction gearbox (111) intended to rotate at least one propulsion member (105) of the aircraft (103). The architecture (101) also comprises at least one low-voltage electrical network (113) with at least one low-voltage electric machine (117, 118) mounted on the reduction gearbox (111) or on the turbomachine (107) and a high-voltage electrical network (125) with high-voltage electric machines (129) mounted on the turbomachine (107).

IPC Classes  ?

  • B64D 27/10 - Aircraft characterised by the type or position of power plant of gas-turbine type
  • B64D 27/24 - Aircraft characterised by the type or position of power plant using steam, electricity, or spring force
  • H02J 1/08 - Three-wire systems; Systems having more than three wires
  • H02J 4/00 - Circuit arrangements for mains or distribution networks not specified as ac or dc

47.

COLLECTOR FOR A DRAINED LIQUID FOR AN AIRCRAFT TURBINE ENGINE AND ASSOCIATED TURBINE ENGINE

      
Application Number FR2023000047
Publication Number 2023/209284
Status In Force
Filing Date 2023-04-24
Publication Date 2023-11-02
Owner SAFRAN HELICOPTER ENGINES (France)
Inventor
  • Francez, Xavier Serge Gaston
  • Benezech, Philippe Jean René Marie
  • Meyere, Nicolas René
  • Perra, Nicolas Christophe
  • Cladiere, Mathieu Pierre

Abstract

The invention relates to a collector (10) for a drained liquid for a turbine engine, comprising: - an internal cavity (54) comprising a first space (54A) for collecting the liquid and a second space (54B) for transferring the liquid, the internal cavity extending longitudinally along a first direction (Z) between a first end closed by a bottom wall (16) of the collector and a second end closed by a cover (14); and - at least one inlet (44) for the drained liquid; the first and second spaces being separated by a partition (56) with a means (58) disposed therein for restricting the passage of the drained liquid from the first space to the second space; wherein the means (58) for restricting the passage of the drained liquid is mounted such that it can be removed from the collector by moving it in the direction from the bottom wall to the cover of the collector.

IPC Classes  ?

  • F01D 25/18 - Lubricating arrangements
  • F01D 25/32 - Collecting of condensation water; Drainage
  • F01M 11/04 - Filling or draining lubricant of or from machines or engines

48.

PROPULSION UNIT WITH FOLDABLE PROPELLER BLADES AND METHOD FOR STOPPING THE PROPELLER IN AN INDEXED ANGULAR POSITION

      
Application Number 18001668
Status Pending
Filing Date 2021-06-10
First Publication Date 2023-11-02
Owner SAFRAN HELICOPTER ENGINES (France)
Inventor
  • Besse, Jean-Louis Robert Guy
  • Serghine, Camel

Abstract

A propulsion unit having a propeller for an aircraft including a nacelle; a propeller mounted in the nacelle so as to be capable of rotating about a longitudinal axis of rotation, the propeller having blades mounted by a root so as to be capable of pivoting between a deployed position, in which they extend radially relative to the axis of rotation, and a folded position, in which they are longitudinally received against the nacelle; drive means that rotate the propeller; indexing means for stopping the propeller in at least one indexed angular position relative to the nacelle; the propulsion unit wherein the indexing means consist of a stepping electric motor including a rotor that is coupled to the propeller.

IPC Classes  ?

  • B64D 35/00 - Transmitting power from power plant to propellers or rotors; Arrangements of transmissions
  • B64D 27/24 - Aircraft characterised by the type or position of power plant using steam, electricity, or spring force
  • B64C 27/50 - Blades foldable to facilitate stowage of aircraft
  • B64C 27/54 - Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement

49.

COLLECTOR FOR A DRAINED LIQUID FOR AN AIRCRAFT TURBINE ENGINE AND ASSOCIATED TURBINE ENGINE

      
Application Number FR2023000048
Publication Number 2023/209285
Status In Force
Filing Date 2023-04-24
Publication Date 2023-11-02
Owner SAFRAN HELICOPTER ENGINES (France)
Inventor
  • Benezech, Philippe Jean René Marie
  • Meyere, Nicolas Rene
  • Perra, Nicolas Christophe
  • Cladiere, Mathieu Pierre

Abstract

The invention relates to a collector (10) for a drained liquid for an aircraft turbine engine, said collector comprising: - an internal cavity (54) comprising a first space (54A) for collecting the drained liquid and a second space (54B) for transferring the collected liquid to a recovery outlet (30); - at least one inlet (44) for the drained liquid, in fluid communication with the first space; and - at least one recovery outlet in fluid communication with the second space; wherein the first space and the second space are separated from each other by a partition (56) with a means (58) disposed therein for restricting the passage of the drained liquid from the first space to the second space, the air in the first space being in communication with the air in the second second space such that the air pressure in the first and second spaces is identical.

IPC Classes  ?

50.

FREE TURBINE TURBOGENERATOR COMPRISING A REVERSIBLE ELECTRICAL MACHINE COUPLED TO THE FREE TURBINE

      
Application Number 18251031
Status Pending
Filing Date 2021-10-25
First Publication Date 2023-10-12
Owner SAFRAN HELICOPTER ENGINES (France)
Inventor
  • Vive, Loïs Pierre Denis
  • Drouin, Thomas
  • Bedrine, Olivier

Abstract

Disclosed is a turbogenerator, in particular for an electrically-driven rotary wing aircraft, comprising a gas generator equipped with a first shaft, at least one reversible electrical machine, and a free turbine provided with a second shaft and caused to rotate by a gas flow generated by the gas generator. The second shaft is coupled to the at least one electrical machine during all phases of operation of the turbomachine, and the turbomachine further comprises a single mechanical coupling means for coupling the first mechanical shaft to the second mechanical shaft when the electrical machine is operating in motor mode and mechanically uncoupling the first mechanical shaft from the second mechanical shaft when the electrical machine is operating in generator mode.

IPC Classes  ?

  • F01D 15/10 - Adaptations for driving, or combinations with, electric generators
  • B64D 41/00 - Power installations for auxiliary purposes

51.

AIRCRAFT TURBOMACHINE COMPRISING A BEARING SUPPORT HAVING AN IMPROVED DESIGN

      
Application Number FR2023050466
Publication Number 2023/194677
Status In Force
Filing Date 2023-03-31
Publication Date 2023-10-12
Owner SAFRAN HELICOPTER ENGINES (France)
Inventor
  • Debat, Alexandre
  • Christophe, Antoine Bernard
  • Robert, Olivier
  • Combebias, Sébastien Mathieu

Abstract

The invention relates to an assembly for an aircraft turbomachine (20), the assembly comprising a stator section (26), a first bearing (28a), a second bearing (28b) and a holder part (32) in an oil chamber (22) delimited by an outer chamber-delimiting portion (24) incorporated into the stator section (26), the holder part (32) comprising: - a first axial end portion (34a) forming an outer ring (36) of the first bearing (28a) or supporting such a ring (36); - a second axial end portion (34b) forming an outer ring of the second bearing (28b) or supporting such a ring, an oil squeeze film damper (50) being arranged between the second portion (34b) and the stator section (26); - an intermediate ring (46) arranged axially between the first and second portions (34a, 34b) and forming a flexible connection and an oil-splash protection element.

IPC Classes  ?

  • F01D 25/18 - Lubricating arrangements
  • F01D 25/16 - Arrangement of bearings; Supporting or mounting bearings in casings

52.

Turbomachine having a free turbine comprising electric machines assisting a gas generator and a free turbine

      
Application Number 18252278
Grant Number 11846198
Status In Force
Filing Date 2021-11-12
First Publication Date 2023-10-12
Grant Date 2023-12-19
Owner SAFRAN HELICOPTER ENGINES (France)
Inventor
  • Vive, Loïs Pierre Denis
  • Bedrine, Olivier
  • Drouin, Thomas

Abstract

A turbomachine, particularly for a rotary-wing aircraft, including a gas generator provided with a rotary shaft, a first reversible electric machine, a power turbine rotationally driven by a stream of gas generated by the gas generator, at least one accessory from among an oil pump and a fuel pump, an accessory gearbox comprising a gear train configured to drive said at least one accessory, and a second electric machine. The second electric machine is reversible, said first electric machine is mechanically coupled to the gas generator, the accessory gearbox and the second electric machine are mechanically coupled to the power turbine, and the turbomachine is devoid of any kinematic coupling between the gear train of the accessory gearbox and the shaft of the gas generator.

IPC Classes  ?

  • F01D 15/10 - Adaptations for driving, or combinations with, electric generators
  • F02C 7/32 - Arrangement, mounting, or driving, of auxiliaries
  • F02C 7/275 - Mechanical drives

53.

AIRCRAFT ELECTRICAL MACHINE WITH IMPROVED HEAT TRANSFER BY MEANS OF A PHASE CHANGE MATERIAL AND ASSOCIATED METHOD

      
Application Number 18042157
Status Pending
Filing Date 2021-08-13
First Publication Date 2023-10-05
Owner
  • SAFRAN HELICOPTER ENGINES (France)
  • SAFRAN (France)
Inventor
  • Serghine, Camel
  • Klonowski, Thomas
  • Quinio, Pierre Gabriel Marie
  • Ayat, Sabrina Siham
  • Rouland, Eric
  • Yon, Sébastien
  • Mutabazi, Albert

Abstract

A method for protecting coils from excessive heating in an aircraft electrical machine comprising a stator (12) and a rotor (14) configured to be rotationally driven with respect to one another, the stator including a plurality of notches (120) receiving one and the same plurality or otherwise of coils, the method including the following successive steps: inserting an electrical insulator (16) into the notches or onto the teeth of the stator, installing the coils (18) in the notches or on the teeth of the stator, casting a phase change material (20) in the notches or on the teeth equipped with the coils, the electrical insulator forming a casting mold.

IPC Classes  ?

  • H02K 15/12 - Impregnating, heating or drying of windings, stators, rotors or machines
  • H02K 3/34 - Windings characterised by the shape, form or construction of the insulation between conductors or between conductor and core, e.g. slot insulation
  • H02K 15/02 - Methods or apparatus specially adapted for manufacturing, assembling, maintaining or repairing of dynamo-electric machines of stator or rotor bodies

54.

MODULE FOR AN AIRCRAFT TURBINE ENGINE

      
Application Number FR2023050414
Publication Number 2023/180668
Status In Force
Filing Date 2023-03-23
Publication Date 2023-09-28
Owner SAFRAN HELICOPTER ENGINES (France)
Inventor
  • Votie, Sylvain Pierre
  • Pardo, Frédéric Philippe Jean-Jacques

Abstract

The invention relates to a turbine engine module, in particular an aircraft turbine engine (10), comprising: - an annular casing (52) having an internal wall (53) forming a channel wall; and - a nozzle (32) surrounded by the casing and comprising an annular external platform (36) and an annular internal platform (37) between which stator blades (34) extend, the external platform having an external face (36b) that faces the internal wall of the casing and comprises an annular groove (60) oriented towards the outside and housing a sealing device (64), the sealing device coming into cylindrical contact with a track (66) of the internal wall (53) of the casing, the module being characterised in that the internal wall (53) of the casing comprises a thermal barrier (70) made of ceramic material directly above the track (66), the track being arranged between the thermal barrier and the sealing device.

IPC Classes  ?

  • F01D 25/24 - Casings; Casing parts, e.g. diaphragms, casing fastenings
  • F01D 9/04 - Nozzles; Nozzle boxes; Stator blades; Guide conduits forming ring or sector
  • F01D 11/00 - Preventing or minimising internal leakage of working fluid, e.g. between stages

55.

IMPROVED TURBOMACHINE FOR A HYBRID AIRCRAFT

      
Application Number FR2023050300
Publication Number 2023/175254
Status In Force
Filing Date 2023-03-07
Publication Date 2023-09-21
Owner SAFRAN HELICOPTER ENGINES (France)
Inventor Fulleringer, Benjamin, Nicolas

Abstract

The invention relates to a turbomachine (100) for a hybrid aircraft, the turbomachine comprising a gas generator (12) carried by a generator shaft (14), at least one free turbine (11) carried by a turbine shaft (13) and rotated by a gas flow generated by the gas generator (12), a main rotor (60), and at least one reversible electric machine (30), the turbine shaft (13) being a through-shaft and extending axially between a first end engaged with the electric machine (30) and a second end engaged with the main rotor (60).

IPC Classes  ?

  • F02C 3/10 - Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor with another turbine driving an output shaft but not driving the compressor
  • F02C 7/275 - Mechanical drives
  • F02C 3/14 - Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant

56.

LUBRICATION AND COOLING OF EQUIPMENT OF AN AIRCRAFT TURBOMACHINE

      
Application Number FR2023050374
Publication Number 2023/175282
Status In Force
Filing Date 2023-03-16
Publication Date 2023-09-21
Owner SAFRAN HELICOPTER ENGINES (France)
Inventor
  • Fulleringer, Benjamin Nicolas
  • Herran, Nicolas Maurice Marcel

Abstract

The invention relates to an aircraft turbomachine (10) comprising: a gas generator (12) comprising an output shaft (26) as well as a first lubricating circuit (28); and equipment (14) coupled to the output shaft (26) and comprising a rotor (38) which is rotationally guided by at least one rolling bearing (40), the equipment (14) comprising a second lubricating circuit (46) which is independent of the first lubricating circuit (28) and which is configured to lubricate the rolling bearing (40), the equipment further comprising a system (50) for cooling the rolling bearing (40), the cooling system (50) being configured to circulate oil in the region of at least one ring (40b) of the rolling bearing, characterized in that the cooling system (50) is independent of the second lubricating circuit (46) and is connected to the first lubricating circuit (28).

IPC Classes  ?

57.

IMPROVED PROPULSIVE ASSEMBLY FOR A MULTI-ENGINE HYBRID AIRCRAFT

      
Application Number FR2023050247
Publication Number 2023/166256
Status In Force
Filing Date 2023-02-21
Publication Date 2023-09-07
Owner SAFRAN HELICOPTER ENGINES (France)
Inventor
  • Fulleringer, Benjamin, Nicolas
  • Moutaux, Antoine, Pascal
  • Thiriet, Romain, Jean, Gilbert

Abstract

A propulsive assembly (100) for a multi-engine hybrid aircraft, comprising a first and a second gas turbine (10, 20) each having a gas generator (12, 22) and a free turbine (11, 21), a main rotor (62) coupled to the free turbine (11, 21) via a first and a second main coupling means (51, 52), a first and a second reversible electric machine (30, 40) each coupled to the gas generator (12, 22) via a first deactivatable coupling means (31, 41), and each coupled to the main rotor (62) via a second deactivatable coupling means (32, 42), the first deactivatable coupling means (31, 41) being activated when the electric machines (30, 40) rotate in a first direction of rotation, and the second deactivatable coupling means (32, 42) being activated when the electric machines (30, 40) rotate in a second direction of rotation opposite to the first direction of rotation.

IPC Classes  ?

  • B64D 35/08 - Transmitting power from power plant to propellers or rotors; Arrangements of transmissions characterised by the transmission being driven by a plurality of power plants
  • B64D 27/24 - Aircraft characterised by the type or position of power plant using steam, electricity, or spring force
  • F02C 7/36 - Power transmission between the different shafts of the gas-turbine plant, or between the gas-turbine plant and the power user
  • F01D 15/10 - Adaptations for driving, or combinations with, electric generators

58.

CIRCULAR MODULAR TRAY FOR THE ADDITIVE MANUFACTURING OF A PART WITH AN AXIS OF REVOLUTION ON A POWDER BED

      
Application Number 18002896
Status Pending
Filing Date 2021-06-11
First Publication Date 2023-08-24
Owner
  • SAFRAN HELICOPTER ENGINES (France)
  • SAFRAN TRANSMISSION SYSTEMS (France)
Inventor
  • Nifenecker, Arnaud Georges
  • Ador, Jérémi Christophe Benjamin
  • Aycaguer, Frédéric
  • Dufau, Frédéric Jacques
  • Gouin, Gilles Gaston Jacques

Abstract

A circular modular tray for the additive manufacturing of a part with an axis of revolution on a powder bed, characterised in that it consists of an assembly of modules that are concentrically coupled along a contiguous axis in a radial direction, the modules including an annular peripheral module and a circular central module.

IPC Classes  ?

  • B22F 12/37 - Rotatable
  • B22F 10/68 - Cleaning or washing
  • B22F 10/66 - Treatment of workpieces or articles after build-up by mechanical means
  • B29C 64/245 - Platforms or substrates
  • B29C 64/35 - Cleaning
  • B33Y 30/00 - ADDITIVE MANUFACTURING, i.e. MANUFACTURING OF THREE-DIMENSIONAL [3D] OBJECTS BY ADDITIVE DEPOSITION, ADDITIVE AGGLOMERATION OR ADDITIVE LAYERING, e.g. BY 3D PRINTING, STEREOLITHOGRAPHY OR SELECTIVE LASER SINTERING - Details thereof or accessories therefor
  • B33Y 40/20 - Post-treatment, e.g. curing, coating or polishing
  • B33Y 10/00 - Processes of additive manufacturing

59.

Production by additive manufacturing of complex parts

      
Application Number 18002011
Grant Number 11988385
Status In Force
Filing Date 2021-06-09
First Publication Date 2023-08-17
Grant Date 2024-05-21
Owner SAFRAN HELICOPTER ENGINES (France)
Inventor
  • Autret, Jean-Paul Didier
  • Gresy, Thomas Sebastien Alexandre
  • Lavignotte, Stéphane
  • Savary, Nicolas Roland Guy

Abstract

A gas turbomachine combustion chamber includes bridges extending side by side to connect in one piece a radially inner wall and a radially outer wall towards a free end of the radially inner wall. The bridges, inner wall, and outer wall have an additive layer structure.

IPC Classes  ?

  • F23R 3/00 - Continuous combustion chambers using liquid or gaseous fuel
  • B33Y 80/00 - Products made by additive manufacturing

60.

HYBRID TURBOMACHINE FOR AIRCRAFT WITH AN ACTIVE ACOUSTIC CONTROL SYSTEM

      
Application Number 18044056
Status Pending
Filing Date 2021-09-03
First Publication Date 2023-08-17
Owner
  • SAFRAN HELICOPTER ENGINES (France)
  • SAFRAN ELECTRICAL & POWER (France)
  • SAFRAN POWER UNITS (France)
Inventor
  • Thiriet, Romain Jean Gilbert
  • Bouty, Eric Jean-Louis
  • Real, Denis Antoine Julien
  • Chau, Valéry

Abstract

Hybrid turbomachine comprising an electric generator, a gas generator equipped with an air inlet and with an exhaust and an acoustic monitoring system comprising a control unit and a plurality of loudspeakers. Hybrid turbomachine comprising an electric generator, a gas generator equipped with an air inlet and with an exhaust and an acoustic monitoring system comprising a control unit and a plurality of loudspeakers. At least a first loudspeaker is disposed on the electric generator, and/or at least a second loudspeaker is disposed on the air inlet of the gas generator, and/or at least a third loudspeaker is disposed on the exhaust of the gas generator. Hybrid turbomachine comprising an electric generator, a gas generator equipped with an air inlet and with an exhaust and an acoustic monitoring system comprising a control unit and a plurality of loudspeakers. At least a first loudspeaker is disposed on the electric generator, and/or at least a second loudspeaker is disposed on the air inlet of the gas generator, and/or at least a third loudspeaker is disposed on the exhaust of the gas generator. The control unit of the acoustic monitoring system is mounted on the electric generator and is configured to make an AC-DC electrical conversion of the electromotive force of the electric generator into an adjustable DC voltage intended to be distributed to loads or to energy storage means.

IPC Classes  ?

  • F02C 7/045 - Air intakes for gas-turbine plants or jet-propulsion plants having provisions for noise suppression
  • B64D 27/10 - Aircraft characterised by the type or position of power plant of gas-turbine type
  • B64D 27/24 - Aircraft characterised by the type or position of power plant using steam, electricity, or spring force
  • B64D 33/02 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
  • F01D 15/10 - Adaptations for driving, or combinations with, electric generators
  • H04R 29/00 - Monitoring arrangements; Testing arrangements

61.

VISUAL REMINDER SYSTEM FOR A FILTER ELEMENT

      
Application Number FR2023050085
Publication Number 2023/148441
Status In Force
Filing Date 2023-01-20
Publication Date 2023-08-10
Owner SAFRAN HELICOPTER ENGINES (France)
Inventor
  • Perra, Nicolas Christophe
  • Cladiere, Mathieu Pierre

Abstract

One aspect of the invention relates to a filtering device (10) for a turbomachine, the device comprising: - a filter support (14); - a removable filter (18) co-operating with the filter support; - a cover (12); - an indicator pin (16); the device comprising a plate (13) that is translatably movable relative to the cover and relative to the indicator pin, the plate being translatably movable between two positions: - a first position such that the plate bears against the removable filter and the indicator pin is in a retracted position; - a second position such that the plate is remote from the cover due to the absence of the removable filter and the indicator pin is in an extended position.

IPC Classes  ?

62.

PROPULSION UNIT WITH FOLDABLE PROPELLER BLADES AND METHOD FOR FOLDING THE BLADES

      
Application Number 18001617
Status Pending
Filing Date 2021-06-14
First Publication Date 2023-08-10
Owner SAFRAN HELICOPTER ENGINES (France)
Inventor
  • Besse, Jean-Louis Robert Guy
  • Serghine, Camel

Abstract

A propulsion unit with a propeller includes a nacelle; a propeller rotatably mounted in the nacelle by means of a hub. The propeller has blades mounted in a blade cuff that is pivotable about a pitch axis relative to the hub. Each blade is pivotable relative to the cuff about a folding axis. A folding device includes an actuator for folding the blades. The folding device includes a control member rotationally affixed to the blade cuff and driven by the actuator. A connecting rod is pivotably mounted, on the one hand, on a root of the associated blade and, on the other hand, on the movable control member.

IPC Classes  ?

  • B64C 27/50 - Blades foldable to facilitate stowage of aircraft
  • B64D 29/00 - Power-plant nacelles, fairings, or cowlings

63.

METHOD FOR STARTING AN AIRCRAFT ENGINE

      
Application Number 18004577
Status Pending
Filing Date 2021-07-06
First Publication Date 2023-08-03
Owner SAFRAN HELICOPTER ENGINES (France)
Inventor
  • Serghine, Camel
  • Robert, Olivier
  • Klonowski, Thomas
  • Seve, Caroline Maud Léna

Abstract

A method for starting an aircraft engine in which the engine is coupled to a lubrication circuit including an oil pump system, the lubrication circuit being constructed and arranged to circulate oil in the engine, and in which an operating mode of the engine includes a stop mode and a standby mode, the starting method including, during a starting phase, measuring an oil temperature, the measurement being performed by a temperature detection device; depending on the temperature measured, compared to a threshold temperature, and depending on the operating mode of the engine, select a starting oil flow profile to be applied in said engine, the selection being performed by a calculator, and applying the selected starting oil flow profile by the oil pump system, the oil pump system being controlled by the calculator.

IPC Classes  ?

  • F16N 29/02 - Special means in lubricating arrangements or systems providing for the indication or detection of undesired conditions; Use of devices responsive to conditions in lubricating arrangements or systems for influencing the supply of lubricant
  • F02C 7/06 - Arrangement of bearings; Lubricating
  • F02C 7/26 - Starting; Ignition

64.

PROPULSION UNIT WITH FOLDABLE PROPELLER BLADES AND METHOD FOR FOLDING THE BLADES

      
Application Number 18001688
Status Pending
Filing Date 2021-06-14
First Publication Date 2023-07-27
Owner SAFRAN HELICOPTER ENGINES (France)
Inventor
  • Besse, Jean-Louis Robert Guy
  • Serghine, Camel

Abstract

A propulsion unit with a propeller is provided, having a nacelle and a propeller rotatably mounted in the nacelle by a hub. The propeller includes blades mounted in a blade cuff pivotable about a pitch axis relative to the hub, each blade being pivotable relative to the cuff about a folding axis. The propulsion unit can further include a folding device that comprises an actuator for folding the blades. The folding device can include a control member rotationally affixed to the blade cuff and driven by the actuator, and a connecting rod pivotably mounted, on the one hand, on a root of the associated blade and, on the other hand, on the movable control member.

IPC Classes  ?

  • B64C 11/28 - Collapsible or foldable blades
  • B64C 11/06 - Blade mountings for variable-pitch blades
  • B64C 27/28 - Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with forward-propulsion propellers pivotable to act as lifting rotors
  • B64C 29/02 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis vertical when grounded

65.

RECUPERATED-CYCLE TURBOSHAFT ENGINE

      
Application Number FR2023050001
Publication Number 2023/135378
Status In Force
Filing Date 2023-01-02
Publication Date 2023-07-20
Owner SAFRAN HELICOPTER ENGINES (France)
Inventor Pons, Bernard Claude

Abstract

The invention relates to a turboshaft engine (1) for an aircraft (2) comprising: - a gas generator (3) comprising a compressor (4), a combustion chamber (5) and an expansion turbine (6); - a power turbine (8) rotating a power take-off (9) by means of a reduction gear (10); - a heat exchanger (11) comprising a first circuit (12) and a second circuit (17); characterised in that the compressor (4) comprises a first shaft (22) rotated by a second shaft (23) of the expansion turbine (6) by means of a transmission mechanism (24), the transmission mechanism (24) and the reduction gear (10) forming part of a gearbox (25) which is arranged axially at a front end (20) of the turboshaft engine (1), such that the compressor (4) is arranged axially between the gearbox (25) and the power turbine (8). Drawing_references_to_be_translated

IPC Classes  ?

  • F02C 3/107 - Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor with two or more rotors connected by power transmission
  • F02C 7/08 - Heating air supply before combustion, e.g. by exhaust gases
  • F02C 7/32 - Arrangement, mounting, or driving, of auxiliaries
  • F02C 7/36 - Power transmission between the different shafts of the gas-turbine plant, or between the gas-turbine plant and the power user

66.

DC-TO-DC CONVERTER FOR AN ELECTRICAL AIRCRAFT PROPULSION SYSTEM

      
Application Number FR2022052514
Publication Number 2023/131755
Status In Force
Filing Date 2022-12-27
Publication Date 2023-07-13
Owner
  • SAFRAN HELICOPTER ENGINES (France)
  • CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE (France)
  • UNIVERSITE DE LORRAINE (France)
Inventor
  • Barraco, Thomas Michel André Gérard
  • Klonowski, Thomas
  • Pierfederici, Serge Lionel
  • Weber, Mathieu Robert

Abstract

The invention relates to a DC-to-DC converter (209) for an electrical aircraft propulsion system designed to be connected in series with an electrical energy storage unit of the electrical propulsion system. The DC-to-DC converter (209) comprises an inverter (401), a transformer (403) and a rectifier (405), and further comprises a current source (417) that is connected to the rectifier (405) and is configured to control the power passing through the DC-to-DC converter (209). The transformer (403) comprises a primary (403a) and two secondaries (403b, 403c), the two secondaries (403b, 403c) sharing a common terminal (407) designed to be connected to a high-voltage DC bus (207) of the electrical propulsion system (201) and two other terminals (409, 411) that are connected to the rectifier (405). The rectifier (405) comprises two arms comprising at least two transistors (415a, 415b, 415c, 415d) that are each in series and are connected, on the one hand, to the two other terminals (409, 411) of the transformer (403) and, on the other hand, to the current source (417).

IPC Classes  ?

  • H02M 3/335 - Conversion of dc power input into dc power output with intermediate conversion into ac by static converters using discharge tubes with control electrode or semiconductor devices with control electrode to produce the intermediate ac using devices of a triode or a transistor type requiring continuous application of a control signal using semiconductor devices only
  • H02J 7/00 - Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
  • B64D 27/24 - Aircraft characterised by the type or position of power plant using steam, electricity, or spring force
  • H02M 7/219 - Conversion of ac power input into dc power output without possibility of reversal by static converters using discharge tubes with control electrode or semiconductor devices with control electrode using devices of a triode or transistor type requiring continuous application of a control signal using semiconductor devices only in a bridge configuration

67.

RECOVERED-CYCLE AIRCRAFT TURBOMACHINE

      
Application Number 18001441
Status Pending
Filing Date 2021-06-15
First Publication Date 2023-07-13
Owner SAFRAN HELICOPTER ENGINES (France)
Inventor
  • Pons, Bernard Claude
  • Puerto, Alphonse
  • Tarnowski, Laurent Pierre
  • Vive, Lois Pierre Denis

Abstract

Aircraft turbomachine including a centrifugal compressor, a combustion chamber, the combustion chamber being supplied by the compressor via a diffuser and via a straightener, and a heat exchanger, the exchanger including a first circuit, supplied with exhaust gas from the turbomachine, and a second circuit, which are connected by volutes on the one hand to an outlet of the diffuser and on the other hand to an inlet of the straightener, the volutes having reversed winding directions such that their connection ports to the exchanger are independent of one another and are substantially diametrically opposed, and such that the minimum cross section of each duct is situated at a larger cross section of the other duct.

IPC Classes  ?

  • F02C 3/10 - Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor with another turbine driving an output shaft but not driving the compressor
  • F02C 7/08 - Heating air supply before combustion, e.g. by exhaust gases

68.

Recovered-cycle aircraft turbomachine

      
Application Number 18001677
Grant Number 11988112
Status In Force
Filing Date 2021-06-15
First Publication Date 2023-07-13
Grant Date 2024-05-21
Owner Safran Helicopter Engines (France)
Inventor
  • Pons, Bernard Claude
  • Puerto, Alphonse
  • Tarnowski, Laurent Pierre
  • Vive, Loïs Pierre Denis

Abstract

An aircraft turbomachine having a centrifugal compressor, an annular combustion chamber, an annular casing extending around the chamber and delimiting an annular space (E) in which the chamber is situated, and a heat exchanger. The heat exchanger can include a first circuit supplied with exhaust gas from the turbomachine, and a second circuit connected by first and second volutes respectively to an outlet of the compressor and to the annular space. The first and second volutes can be positioned at an axial distance from one another, and the second volute can be connected to the annular space by a straightener which is situated at least in part outside the casing and which is integrated into an annular connecting pipe which connects the second volute to this casing.

IPC Classes  ?

  • F01D 9/02 - Nozzles; Nozzle boxes; Stator blades; Guide conduits

69.

HYDRAULIC TORQUE MEASUREMENT DEVICE FOR AIRCRAFT ENGINE UNIT

      
Application Number 17998885
Status Pending
Filing Date 2021-05-09
First Publication Date 2023-07-06
Owner SAFRAN HELICOPTER ENGINES (France)
Inventor Houssaye, Laurent Louis Sylvain

Abstract

A hydraulic torque measurement device for an aircraft engine unit includes a hermetically sealed enclosure having a rigid wall and a deformable wall that define an internal volume. The device further includes at least one pressure measuring element capable of measuring the pressure prevailing in the internal volume. The hydraulic torque measuring device allows a service state in which the internal volume is filled exclusively with an incompressible liquid, and in which the deformable wall is configured to be subjected to a pressure force. In some embodiments, the hydraulic torque measurement device is suitable for use with a gearbox.

IPC Classes  ?

  • G01L 3/14 - Rotary-transmission dynamometers wherein the torque-transmitting element is other than a torsionally-flexible shaft
  • G01L 5/12 - Apparatus for, or methods of, measuring force, work, mechanical power, or torque, specially adapted for specific purposes for measuring axial thrust in a rotary shaft, e.g. of propulsion plants

70.

AIRCRAFT TURBOMACHINE COMPRISING A DEVICE FOR INHIBITING THE ACCUMULATION OF COKE IN A DUCT

      
Application Number FR2022052466
Publication Number 2023/118750
Status In Force
Filing Date 2022-12-21
Publication Date 2023-06-29
Owner SAFRAN HELICOPTER ENGINES (France)
Inventor
  • Fulleringer, Benjamin Nicolas
  • Debat, Alexandre
  • Fonts, Pierre-Marie
  • Robert, Olivier

Abstract

An aircraft turbomachine (10) having a gas generator (12) comprising, along a longitudinal axis (X), at least one compressor (14), a combustion chamber (16) and at least one turbine (18), the turbomachine (10) further having at least one duct (20) for supplying liquid to at least one member chosen from an oil jet (22) and a fuel injector (50), this duct (20) having rectilinear portions (21a, 21b) and bent portions (21c, 21d) and comprising at least one region in which the liquid is liable to coke, characterized in that it comprises at least one turbulence element (40-48) in the at least one region in the duct.

IPC Classes  ?

  • F01D 9/06 - Fluid supply conduits to nozzles or the like
  • F01D 25/18 - Lubricating arrangements
  • F02C 7/22 - Fuel supply systems
  • F16L 55/24 - Preventing accumulation of dirt or other matter in pipes, e.g. by traps, by strainers
  • B08B 9/032 - Cleaning the internal surfaces; Removal of blockages by the mechanical action of a moving fluid, e.g. by flushing

71.

Method for quickly stopping the rotor of a helicopter after landing

      
Application Number 17754885
Grant Number 11852023
Status In Force
Filing Date 2020-10-14
First Publication Date 2023-06-22
Grant Date 2023-12-26
Owner SAFRAN HELICOPTER ENGINES (France)
Inventor
  • Bedrine, Olivier
  • Bazet, Jean Michel Frédéric Louis
  • Cazaux, David

Abstract

A method for quickly stopping the propulsion rotor of a helicopter after landing, comprising, following a request for quickly stopping the engine by a helicopter pilot, the following steps managed by the control unit of the turbomachine: Detecting the absence of the thermal stabilization phase of the gas generator of at least one turbomachine, controlling an extinction of the combustion chamber of the gas generator of at least one turbomachine, maintaining the rotation of the gas generator of which the combustion chamber is extinguished by means of said at least one electrical machine to ventilate the gas generator and stopping the main rotor of the helicopter by means of a mechanical brake.

IPC Classes  ?

  • F01D 21/12 - Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to temperature
  • F02C 7/25 - Fire protection or prevention

72.

METHOD FOR REGULATING THE SPEED OF ROTATION OF A PROPULSION DEVICE OF A HYBRID PROPULSION UNIT FOR AN AIRCRAFT, IN THE EVENT OF A FAILURE OF THE MAIN REGULATION SYSTEM OF THE HEAT ENGINE OF THE HYBRID PROPULSION UNIT

      
Application Number FR2022052330
Publication Number 2023/111445
Status In Force
Filing Date 2022-12-13
Publication Date 2023-06-22
Owner SAFRAN HELICOPTER ENGINES (France)
Inventor
  • Lemay, David Bernard Martin
  • Marin, Jean-Philippe Jacques
  • Frealle, Jean-Luc Charles Gilbert

Abstract

The invention relates to a method for regulating the speed of a propulsion device of a hybrid propulsion unit for an aircraft comprising: the propulsion device and an MGB; the heat engine and at least one electric motor, mounted in parallel on the MGB, the heat engine being provided with a fuel circuit; main and backup regulation systems for the heat engine, and a regulation system for the electric motor, each being capable of regulating the speed of the heat engine or the electric motor, respectively; and an aircraft control system, capable of sending a speed or power setpoint to each of the regulation means for the heat engine and the electric motor. The method comprises, when the main regulation system for the heat engine fails and is locked to a QCarbP* fuel flow command: - sending a speed setpoint NM2réf to the regulation system for the electric motor, the regulation system for the electric motor sending a power setpoint PM2* to the electric motor, whereby an instantaneous power PM2m of the electric motor is obtained; - simultaneously, sending a speed or power setpoint to the backup regulation system for the heat engine, the backup regulation system sending a fuel flow command QCarbAux* to the fuel circuit of the heat engine, which command is selected to vary the fuel flow QCarb injected into a combustion chamber of the heat engine according to whether the power PM1 of the heat engine is to be varied.

IPC Classes  ?

73.

CONTROL DEVICE FOR CONTROLLING AN AIRFLOW GUIDING SYSTEM, IN PARTICULAR IN AN AIRCRAFT TURBINE ENGINE

      
Document Number 03238900
Status Pending
Filing Date 2022-12-02
Open to Public Date 2023-06-15
Owner SAFRAN HELICOPTER ENGINES (France)
Inventor
  • Javoy, Thibaut Maxime
  • Baucheff, Christophe Boris

Abstract

The invention relates to a control device (30) for controlling an airflow guiding system (20), comprising: - at least one vane (21) that is rotatable on a shaft (21a) of the vane between a first angle and a second angle; - an actuator (31) comprising a body (32) inside which a piston (32a) is translatably mounted, the piston being rigidly connected to a drive rod (33); - a control rod (34) comprising a downstream end (34a) that is connected to the shaft (21a) of the vane, the actuator (31) being configured to drive the piston (32a) between a first end position (P1') and a second end position (P2') of a nominal operating range and the downstream end (34a) of the control rod (34) between a first end position (P1) and a second end position (P2) of a nominal operating range in which the vane (21) is movable between a first angle and a second angle, the device being characterised in that it comprises a drive mechanism (40) that connects an upstream end (33a) of the drive rod (33) to an upstream end (34b) of the control rod (34), which is opposite the downstream end (34a), and in that the drive mechanism (40) is configured so that, in the event of the control device failing, it places the downstream end (34a) of the control rod (34) in a safety position (PS) located between the first end position (P1) and a second end position (P2) of the nominal operating range and in which the vane (21) is oriented at a safety pitch angle between the first angle and the second angle.

IPC Classes  ?

  • F01D 17/16 - Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
  • F01D 17/20 - Devices dealing with sensing elements or final actuators or transmitting means between them, e.g. power-assisted
  • F04D 29/56 - Fluid-guiding means, e.g. diffusers adjustable

74.

Pre-vaporization tube for a turbine engine combustion chamber

      
Application Number 17766602
Grant Number 11841140
Status In Force
Filing Date 2020-10-05
First Publication Date 2023-06-15
Grant Date 2023-12-12
Owner SAFRAN HELICOPTER ENGINES (France)
Inventor
  • Lederlin, Thomas Jean Olivier
  • Laurent, Christophe
  • Mauries, Guillaume Gerard Joel

Abstract

A pre-vaporisation tube for a turbine engine combustion chamber includes a main body ROOM defining a first inner duct configured to have an injector mounted therein. The tube includes a first end attached to a wall of the chamber, and at least two end pieces are arranged at a second end of the body and define second inner ducts. The end pieces include first portions and second portions, respectively. The second portions each include two coaxial cylindrical walls which are inner and outer coaxial cylindrical walls, respectively, and which define an annular cavity therebetween. The inner wall defines an inner passage and has first openings for fluid communication between the passage and the annular cavity.

IPC Classes  ?

  • F23R 3/28 - Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
  • F23R 3/32 - Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising fuel prevapourising devices being tubular

75.

METHOD FOR CHECKING THE MAXIMUM POWER AVAILABLE TO DIFFERENT MEMBERS OF A PROPULSION CHAIN OF AN AIRCRAFT

      
Application Number EP2022084556
Publication Number 2023/104777
Status In Force
Filing Date 2022-12-06
Publication Date 2023-06-15
Owner SAFRAN HELICOPTER ENGINES (France)
Inventor
  • Darfeuil, Pierre
  • Lemay, David
  • Marin, Jean-Philippe
  • Thiriet, Romain

Abstract

The invention relates to a method for checking the maximum power available to members of a propulsion system of an aircraft (1) comprising first members (M1.1, M2.1, D10, TG, BAT1) that are sized to compensate for the failure of second members of the propulsion system (M1.2, M2.2, D20, TG, BAT2) by delivering a maximum power to keep the aircraft in a safe operating range, the method comprising the following steps for each of the first members: - placing the first member in a state that is substantially equal to a maximum power state (PM); - adjusting the power delivered by the second member working in synergy with the first member so that the first member and the second member contribute to delivering the power required for the aircraft in the flight phase; - determining the power delivered by the first member placed in the maximum power state; - from the determined power, deducing information relating to the maximum power available to the first member.

IPC Classes  ?

  • B64D 31/06 - Initiating means actuated automatically
  • B64D 45/00 - Aircraft indicators or protectors not otherwise provided for
  • B64D 27/24 - Aircraft characterised by the type or position of power plant using steam, electricity, or spring force

76.

CONTROL DEVICE FOR CONTROLLING AN AIRFLOW GUIDING SYSTEM, IN PARTICULAR IN AN AIRCRAFT TURBINE ENGINE

      
Application Number FR2022052231
Publication Number 2023/105143
Status In Force
Filing Date 2022-12-02
Publication Date 2023-06-15
Owner SAFRAN HELICOPTER ENGINES (France)
Inventor
  • Javoy, Thibaut Maxime
  • Baucheff, Christophe Boris

Abstract

The invention relates to a control device (30) for controlling an airflow guiding system (20), comprising: - at least one vane (21) that is rotatable on a shaft (21a) of the vane between a first angle and a second angle; - an actuator (31) comprising a body (32) inside which a piston (32a) is translatably mounted, the piston being rigidly connected to a drive rod (33); - a control rod (34) comprising a downstream end (34a) that is connected to the shaft (21a) of the vane, the actuator (31) being configured to drive the piston (32a) between a first end position (P1') and a second end position (P2') of a nominal operating range and the downstream end (34a) of the control rod (34) between a first end position (P1) and a second end position (P2) of a nominal operating range in which the vane (21) is movable between a first angle and a second angle, the device being characterised in that it comprises a drive mechanism (40) that connects an upstream end (33a) of the drive rod (33) to an upstream end (34b) of the control rod (34), which is opposite the downstream end (34a), and in that the drive mechanism (40) is configured so that, in the event of the control device failing, it places the downstream end (34a) of the control rod (34) in a safety position (PS) located between the first end position (P1) and a second end position (P2) of the nominal operating range and in which the vane (21) is oriented at a safety pitch angle between the first angle and the second angle.

IPC Classes  ?

  • F01D 17/16 - Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
  • F01D 17/20 - Devices dealing with sensing elements or final actuators or transmitting means between them, e.g. power-assisted
  • F04D 29/56 - Fluid-guiding means, e.g. diffusers adjustable

77.

METAL POWDER FOR A POWDER BED ADDITIVE MANUFACTURING PROCESS

      
Application Number FR2022052244
Publication Number 2023/105150
Status In Force
Filing Date 2022-12-05
Publication Date 2023-06-15
Owner
  • SAFRAN AIRCRAFT ENGINES (France)
  • SAFRAN HELICOPTER ENGINES (France)
Inventor
  • Sistach, Hugo, Jean-Louis
  • Lavignotte, Stéphane
  • Colas, Cédric Pierre Jacques
  • Piette, Romaric Jean-Marie

Abstract

The present invention relates to a metal powder for a powder bed additive manufacturing process, the metal powder comprising a nickel-based alloy comprising at least 0.05% carbon, at least 14.25% cobalt, at least 14% chromium, at least 4% aluminium, at least 3.9% molybdenum, at least 3% titanium, at most 0.5% iron, at least 0.012% boron, at most 0.060% zirconium, at most 0.150% manganese, at most 0.2% silicon, at most 0.1% copper, at most 0.5 ppm bismuth, at most 5 ppm silver, at most 5 ppm lead, at most 25 ppm sulphur, at most 200 ppm oxygen, and at most 60 ppm nitrogen.

IPC Classes  ?

  • B22F 1/05 - Metallic powder characterised by the size or surface area of the particles
  • B22F 5/00 - Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product
  • B22F 5/04 - Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product of turbine blades
  • B22F 10/28 - Powder bed fusion, e.g. selective laser melting [SLM] or electron beam melting [EBM]
  • B22F 10/36 - Process control of energy beam parameters
  • B22F 10/366 - Scanning parameters, e.g. hatch distance or scanning strategy
  • B22F 10/64 - Treatment of workpieces or articles after build-up by thermal means
  • B33Y 10/00 - Processes of additive manufacturing
  • B33Y 40/20 - Post-treatment, e.g. curing, coating or polishing
  • B33Y 50/02 - Data acquisition or data processing for additive manufacturing for controlling or regulating additive manufacturing processes
  • B33Y 70/00 - Materials specially adapted for additive manufacturing
  • B33Y 80/00 - Products made by additive manufacturing
  • C22C 1/04 - Making non-ferrous alloys by powder metallurgy
  • C22C 19/05 - Alloys based on nickel or cobalt based on nickel with chromium
  • C22F 1/10 - Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of nickel or cobalt or alloys based thereon
  • F01D 5/28 - Selecting particular materials; Measures against erosion or corrosion

78.

MODULAR TRAY FOR THE POWDER BED ADDITIVE MANUFACTURING OF A PART WITH AN AXIS OF REVOLUTION

      
Application Number 17995465
Status Pending
Filing Date 2021-03-31
First Publication Date 2023-06-08
Owner
  • SAFRAN HELICOPTER ENGINES (France)
  • SAFRAN TRANSMISSION SYSTEMS (France)
Inventor
  • Nifenecker, Arnaud Georges
  • Ador, Jérémi Christophe Benjamin
  • Aycaguer, Frédéric
  • Dufau, Frédéric Jacques
  • Gouin, Gilles Gaston Jacques
  • Wilmes, Jean-Pierre
  • Arguel, Werner

Abstract

A modular tray, for the additive manufacturing of a part with an axis of revolution on a powder bed, includes: a shaft-mounted circular module including a shaft provided with a circular tray at one of the ends thereof, the shaft and the circular tray being concentric; and a main support module including, in one face, a cavity configured for receiving the shaft-mounted circular module, the shaft being completely inserted in the cavity. The assembly of the shaft-mounted circular module and of the main support module define a planar top surface that is at least partly formed by the circular tray of the shaft-mounted circular module.

IPC Classes  ?

  • B22F 12/37 - Rotatable
  • B22F 10/28 - Powder bed fusion, e.g. selective laser melting [SLM] or electron beam melting [EBM]
  • B22F 10/66 - Treatment of workpieces or articles after build-up by mechanical means
  • B22F 12/82 - Combination of additive manufacturing apparatus or devices with other processing apparatus or devices
  • B22F 10/64 - Treatment of workpieces or articles after build-up by thermal means
  • B33Y 30/00 - ADDITIVE MANUFACTURING, i.e. MANUFACTURING OF THREE-DIMENSIONAL [3D] OBJECTS BY ADDITIVE DEPOSITION, ADDITIVE AGGLOMERATION OR ADDITIVE LAYERING, e.g. BY 3D PRINTING, STEREOLITHOGRAPHY OR SELECTIVE LASER SINTERING - Details thereof or accessories therefor
  • B33Y 40/20 - Post-treatment, e.g. curing, coating or polishing
  • B33Y 10/00 - Processes of additive manufacturing
  • B22F 10/47 - Structures for supporting workpieces or articles during manufacture and removed afterwards characterised by structural features
  • B29C 64/245 - Platforms or substrates
  • B29C 64/153 - Processes of additive manufacturing using only solid materials using layers of powder being selectively joined, e.g. by selective laser sintering or melting
  • B29C 64/30 - Auxiliary operations or equipment

79.

TURBOMACHINE COMPRESSOR HAVING A STATIONARY WALL PROVIDED WITH A SHAPE TREATMENT

      
Application Number 17997955
Status Pending
Filing Date 2021-04-23
First Publication Date 2023-06-08
Owner SAFRAN HELICOPTER ENGINES (France)
Inventor
  • Artus, Fabien Jean-Michel
  • Tarnowski, Laurent Pierre

Abstract

A turbomachine includes a compressor including variable-pitch stationary vanes each extending radially between a rotary hub and a stationary casing surrounding this rotary hub, each variable-pitch vane including a blade having a base spaced apart by a first radial gap from a stationary wall of the casing, and a tip spaced apart by a second radial gap from a rotary wall of the rotary hub. The stationary wall of the casing or the rotary wall of the rotary hub includes at the blade a shape treatment arranged to channel an air leak passing through the corresponding gap.

IPC Classes  ?

  • F04D 29/56 - Fluid-guiding means, e.g. diffusers adjustable
  • F01D 17/16 - Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
  • F04D 29/68 - Combating cavitation, whirls, noise, vibration, or the like; Balancing by influencing boundary layers

80.

SYSTEM AND METHOD FOR AUTOMATICALLY VALIDATING THE RESPONSE COMPLIANCE OF A PENETRANT TESTING LINE

      
Application Number EP2022082156
Publication Number 2023/088974
Status In Force
Filing Date 2022-11-16
Publication Date 2023-05-25
Owner SAFRAN HELICOPTER ENGINES (France)
Inventor
  • Briffa, Patrick Lucien François
  • Juliac, Etienne
  • Guazzone, Laurent Jean-Pascal

Abstract

The invention relates to a system (1) for automatically validating the response compliance of a penetrant testing line by analysing a reference test specimen undergoing dye penetrant testing from said penetrant testing line, the system comprising a casing (2) surrounding all the elements of the system (1), a positioning base (3) for the reference test specimen undergoing dye penetrant testing, at least two ultraviolet lighting devices (4) positioned on either side of the positioning base (3) so as to be able to illuminate it with ultraviolet light, an electronic board, a motorised linear guide (6) controlled by the electronic board and suitable for being able to move the positioning base (3) and hold said base in position in the casing (2), and a monochrome camera (10) having a lens directed towards the positioning base (3).

IPC Classes  ?

  • G01N 21/91 - Investigating the presence of flaws, defects or contamination using penetration of dyes, e.g. fluorescent ink

81.

COMBUSTION ASSEMBLY

      
Application Number 17801766
Status Pending
Filing Date 2021-02-23
First Publication Date 2023-05-18
Owner SAFRAN HELICOPTER ENGINES (France)
Inventor
  • Savary, Nicolas Roland Guy
  • Lailhacar, Christophe
  • Lamaison, Olivier
  • Lavignotte, Stéphane

Abstract

A combustion assembly for a gas turbine includes a flame tube and a fuel supply including a flow rate limiter supplying an injector. The flow rate limiter and the fuel injector are formed in one piece.

IPC Classes  ?

  • F02C 7/22 - Fuel supply systems
  • F02C 9/26 - Control of fuel supply
  • F23D 11/38 - Nozzles; Cleaning devices therefor
  • F23R 3/28 - Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply

82.

Turbomachine hollow blade

      
Application Number 17909143
Grant Number 11808179
Status In Force
Filing Date 2021-03-08
First Publication Date 2023-05-11
Grant Date 2023-11-07
Owner SAFRAN HELICOPTER ENGINES (France)
Inventor
  • Vial, Laurence
  • Frelon, Bruno
  • Beugniez, Jérôme
  • Bellot, Yann

Abstract

Turbomachine hollow blade (11) comprising at least one vane (14) having lateral walls (15) which are intended to guide a flow in a flow path around the vane and which are fixed to a first platform (12) at a first longitudinal end of the vane (14), the vane (14) further comprising an internal cavity between the lateral walls (15), which cavity is intended for passing a vane-cooling fluid, with a fluid inlet opening (19) opening through said first platform (12), characterized in that a gyroid surface network (18) fills at least part of the cavity, being arranged therein so as to guide the cooling fluid, and is in contact with at least part of the lateral walls (15).

IPC Classes  ?

  • F01D 9/06 - Fluid supply conduits to nozzles or the like
  • F01D 5/18 - Hollow blades; Heating, heat-insulating, or cooling means on blades
  • B33Y 80/00 - Products made by additive manufacturing

83.

Propulsion system for an aircraft

      
Application Number 17767576
Grant Number 11932410
Status In Force
Filing Date 2020-10-12
First Publication Date 2023-05-11
Grant Date 2024-03-19
Owner
  • SAFRAN (France)
  • SAFRAN HELICOPTER ENGINES (France)
Inventor
  • Besse, Jean-Louis Robert Guy
  • Maldonado, Ye-Bonne Karina

Abstract

A propulsion system for an aircraft includes a rotor and a nacelle fairing that extends around the rotor in relation to an axis. The nacelle fairing includes an upstream portion forming an inlet section of the nacelle fairing as well as a downstream portion, a downstream end of which forms an outlet section of the nacelle fairing. The downstream portion includes radially inner and outer walls, both of which are made of a deformable shape memory material. The wall has independently actuatable piston actuator mechanisms, each actuator mechanism being actuatable independently of the others and being designed to cooperate with means built into an inner surface of the wall to deform the wall in a radial direction in relation to the axis under the effect of a predetermined displacement command.

IPC Classes  ?

  • B64D 29/00 - Power-plant nacelles, fairings, or cowlings
  • F01D 5/02 - Blade-carrying members, e.g. rotors
  • F01D 25/00 - Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
  • F02K 1/00 - Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto

84.

ELECTROMECHANICAL INSTALLATION FOR AN AIRCRAFT WITH A TURBOGENERATOR, METHOD FOR EMERGENCY SHUTDOWN OF AN AIRCRAFT TURBOGENERATOR AND CORRESPONDING COMPUTER PROGRAM

      
Application Number 18000885
Status Pending
Filing Date 2021-06-14
First Publication Date 2023-05-04
Owner SAFRAN HELICOPTER ENGINES (France)
Inventor
  • Thiriet, Romain Jean Gilbert
  • Lemay, David Bernard Martin

Abstract

An aircraft with an electrical network including electrical subnetworks; a turbo generator including a gas turbine, an electricity generator with permanent magnets having phase groups respectively connected to the electrical subnetworks, and, for each phase group, an isolation device; and a control device designed to detect a short circuit in at least one of the phase groups, each phase group in which a short circuit is detected being described as defective and each other phase group being described as healthy and, in response to the detection of the short circuit, to disconnect this defective phase group from its associated electrical subnetwork and to command the shutdown of the gas turbine. The control device is also designed, in response to the detection of the short circuit, to keep each healthy phase group connected to its electrical subnetwork.

IPC Classes  ?

  • B64D 41/00 - Power installations for auxiliary purposes
  • H02H 7/06 - Emergency protective circuit arrangements specially adapted for specific types of electric machines or apparatus or for sectionalised protection of cable or line systems, and effecting automatic switching in the event of an undesired change from norm for synchronous capacitors

85.

METHOD FOR THE QUANTITATIVE MEASUREMENT OF AN ELEMENT IN A SPECIMEN

      
Application Number FR2022051903
Publication Number 2023/062309
Status In Force
Filing Date 2022-10-10
Publication Date 2023-04-20
Owner SAFRAN HELICOPTER ENGINES (France)
Inventor
  • Vernault, Cyril Roger
  • Anssems, Lucie
  • Besombes, Mariane Erika Michèle
  • Gaulhet, Manon Paule Jeanne

Abstract

The invention relates to a method for the quantitative measurement of an element (4) in a metal test specimen (1) which has received a thermochemical surface treatment, characterised in that the method comprises the following steps: • - a- making a cut in the test specimen; • - b- taking a photograph, using an optical microscope, of said cut on a surface S with magnification; • - c- calculating the ratio of the surfaces s occupied by the element with respect to the surface S in the photograph by means of an image-processing tool; and • - d- obtaining the content of the element in the surface S of the test specimen. A profile of the content of undesirable elements can thus be obtained without the subjective aspect of human checking, which profile is representative of a content obtained by acquiring diffraction of X-rays produced using a synchrotron.

IPC Classes  ?

  • G01N 21/94 - Investigating contamination, e.g. dust
  • G01N 21/95 - Investigating the presence of flaws, defects or contamination characterised by the material or shape of the object to be examined
  • G06T 7/62 - Analysis of geometric attributes of area, perimeter, diameter or volume
  • G06T 7/00 - Image analysis
  • G01N 1/28 - Preparing specimens for investigation
  • G01N 33/204 - Structure thereof, e.g. crystal structure

86.

DEVICE FOR INJECTING DIHYDROGEN AND AIR

      
Document Number 03233988
Status Pending
Filing Date 2022-10-05
Open to Public Date 2023-04-13
Owner
  • CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE (France)
  • SAFRAN HELICOPTER ENGINES (France)
  • UNIVERSITE TOULOUSE III - PAUL SABATIER (France)
Inventor
  • Richard, Stephane Raphael Yves
  • Viguier, Christophe Nicolas Henri
  • Marragou, Sylvain
  • Schuller, Thierry

Abstract

The invention relates to a dihydrogen injection device (2) having a longitudinal axis (X), intended to be mounted on an annular base of an annular combustion chamber (4) of a turbomachine, comprising an inner channel (6) for circulating dihydrogen, and an annular outer channel (8) for circulating a mixture at least comprising air, the inner channel (6) and the annular outer channel (8) being coaxial, an inner swirler (14) being provided in the inner channel (6) and an outer swirler (28) being provided in the annular outer channel (8), a downstream end (16) of the inner channel (6) being arranged upstream, at a distance r, from a downstream end (24) of the annular outer channel (8). Such combustion of dihydrogen makes it possible to eliminate carbon-containing polluting emissions such as carbon monoxide, unburned hydrocarbons or fine particles and smoke particles.

IPC Classes  ?

  • F23R 3/14 - Air inlet arrangements for primary air inducing a vortex by using swirl vanes
  • F23D 14/24 - Non-premix gas burners, i.e. in which gaseous fuel is mixed with combustion air on arrival at the combustion zone with separate air and gas feed ducts, e.g. with ducts running parallel or crossing each other at least one of the fluids being submitted to a swirling motion

87.

DEVICE FOR INJECTING DIHYDROGEN AND AIR

      
Application Number FR2022051883
Publication Number 2023/057722
Status In Force
Filing Date 2022-10-05
Publication Date 2023-04-13
Owner
  • CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE (France)
  • SAFRAN HELICOPTER ENGINES (France)
  • UNIVERSITE DE TOULOUSE III - PAUL SABATIER (France)
Inventor
  • Richard, Stéphane, Raphaël, Yves
  • Viguier, Christophe, Nicolas, Henri
  • Marragou, Sylvain
  • Schuller, Thierry

Abstract

The invention relates to a dihydrogen injection device (2) having a longitudinal axis (X), intended to be mounted on an annular base of an annular combustion chamber (4) of a turbomachine, comprising an inner channel (6) for circulating dihydrogen, and an annular outer channel (8) for circulating a mixture at least comprising air, the inner channel (6) and the annular outer channel (8) being coaxial, an inner swirler (14) being provided in the inner channel (6) and an outer swirler (28) being provided in the annular outer channel (8), a downstream end (16) of the inner channel (6) being arranged upstream, at a distance r, from a downstream end (24) of the annular outer channel (8). Such combustion of dihydrogen makes it possible to eliminate carbon-containing polluting emissions such as carbon monoxide, unburned hydrocarbons or fine particles and smoke particles.

IPC Classes  ?

  • F23R 3/14 - Air inlet arrangements for primary air inducing a vortex by using swirl vanes
  • F23D 14/48 - Nozzles
  • F23R 3/28 - Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
  • F23D 14/24 - Non-premix gas burners, i.e. in which gaseous fuel is mixed with combustion air on arrival at the combustion zone with separate air and gas feed ducts, e.g. with ducts running parallel or crossing each other at least one of the fluids being submitted to a swirling motion

88.

ELECTRIC MOTOR ROTOR

      
Application Number FR2022051730
Publication Number 2023/041873
Status In Force
Filing Date 2022-09-14
Publication Date 2023-03-23
Owner SAFRAN HELICOPTER ENGINES (France)
Inventor
  • Serghine, Camel
  • Klonowski, Thomas

Abstract

The present invention relates to a rotor (1) for an electric motor of an aircraft, the rotor (1) comprising a shaft (2) made of a first material and a conductor assembly (4) made of a second material that differs from the first material, the rotor (1) being characterized in that the shaft (2) has a shoulder portion (6) having at least one longitudinal slot (25) and in that the conductor assembly (4) is a single-piece structure comprising at least one conducting bar (28) intended to be positioned in the at least one slot (25) and including a skin (29) intended to be fastened onto the shoulder portion.

IPC Classes  ?

  • H02K 15/00 - Methods or apparatus specially adapted for manufacturing, assembling, maintaining or repairing of dynamo-electric machines
  • H02K 17/16 - Asynchronous induction motors having rotors with internally short-circuited windings, e.g. cage rotors
  • H02K 17/18 - Asynchronous induction motors having rotors with internally short-circuited windings, e.g. cage rotors having double-cage or multiple-cage rotors
  • H02K 15/02 - Methods or apparatus specially adapted for manufacturing, assembling, maintaining or repairing of dynamo-electric machines of stator or rotor bodies
  • H02K 1/02 - DYNAMO-ELECTRIC MACHINES - Details of the magnetic circuit characterised by the magnetic material

89.

TURBOMACHINE ELEMENT COMPRISING AT LEAST ONE BLADE OBTAINED BY ADDITIVE MANUFACTURING

      
Application Number FR2022051747
Publication Number 2023/041880
Status In Force
Filing Date 2022-09-16
Publication Date 2023-03-23
Owner SAFRAN HELICOPTER ENGINES (France)
Inventor
  • Votie, Sylvain Pierre
  • Boisseleau, Denis, Daniel, Jean
  • Betbeder-Laüque, Xavier, Roger

Abstract

The present invention relates to a turbomachine element (1), comprising at least one blade (2) obtained by additive manufacturing, the blade (2) having a skin (4) and an internal lattice (6) allowing air circulation in the blade (2) and having an additive manufacturing support function for the skin (4).

IPC Classes  ?

  • F01D 5/14 - Form or construction
  • F01D 5/18 - Hollow blades; Heating, heat-insulating, or cooling means on blades
  • F01D 9/06 - Fluid supply conduits to nozzles or the like

90.

TURBOMACHINE ELEMENT COMPRISING AT LEAST ONE BLADE OBTAINED BY ADDITIVE MANUFACTURING

      
Document Number 03231937
Status Pending
Filing Date 2022-09-16
Open to Public Date 2023-03-23
Owner SAFRAN HELICOPTER ENGINES (France)
Inventor
  • Votie, Sylvain Pierre
  • Boisseleau, Denis Daniel Jean
  • Betbeder-Lauque, Xavier Roger

Abstract

The present invention relates to a turbomachine element (1), comprising at least one blade (2) obtained by additive manufacturing, the blade (2) having a skin (4) and an internal lattice (6) allowing air circulation in the blade (2) and having an additive manufacturing support function for the skin (4).

IPC Classes  ?

  • F01D 5/14 - Form or construction
  • F01D 5/18 - Hollow blades; Heating, heat-insulating, or cooling means on blades
  • F01D 9/06 - Fluid supply conduits to nozzles or the like

91.

ELECTRIC MOTOR ROTOR

      
Application Number FR2022051731
Publication Number 2023/041874
Status In Force
Filing Date 2022-09-14
Publication Date 2023-03-23
Owner SAFRAN HELICOPTER ENGINES (France)
Inventor
  • Serghine, Camel
  • Klonowski, Thomas

Abstract

The present invention relates to a rotor (1) of an aircraft electric motor comprising a shaft (2) made of a first material and a skin (4) made of a second material different from the first material, the rotor (1) being characterized in that the shaft (2) has a shoulder portion (6) to which the skin (4) is attached at the shoulder portion (6), the rotor (1) having an interpenetration layer of the first material and of the second material, the interpenetration layer comprising an alloy of the first material and of the second material.

IPC Classes  ?

  • H02K 15/00 - Methods or apparatus specially adapted for manufacturing, assembling, maintaining or repairing of dynamo-electric machines
  • H02K 17/16 - Asynchronous induction motors having rotors with internally short-circuited windings, e.g. cage rotors
  • H02K 15/02 - Methods or apparatus specially adapted for manufacturing, assembling, maintaining or repairing of dynamo-electric machines of stator or rotor bodies
  • H02K 1/02 - DYNAMO-ELECTRIC MACHINES - Details of the magnetic circuit characterised by the magnetic material

92.

METHOD FOR TRAINING TO COPE WITH A FAULT AFFECTING ONE POWERTRAIN OF A HYBRID PROPULSION SYSTEM

      
Application Number FR2022051622
Publication Number 2023/031549
Status In Force
Filing Date 2022-08-29
Publication Date 2023-03-09
Owner SAFRAN HELICOPTER ENGINES (France)
Inventor
  • Lemay, David, Bernard, Martin
  • Marin, Jean-Philippe, Jacques

Abstract

The invention relates to a method for training a pilot to cope with a fault affecting one powertrain of a hybrid propulsion system for an aircraft comprising, connected in parallel to a transmission unit, n powertrains (where n≥2), including a first and a second powertrain that are heterogeneous in nature. It involves, during a flight of the aircraft, simulating a fault affecting the first powertrain while, at the same time as performing the simulation, checking the status of the n powertrains of the propulsion system. If a fault affecting one of the n powertrains is detected, the simulation is halted and the instantaneous power delivered by at least one of either the first or the second powertrain is increased so that the sum of the instantaneous powers delivered by the n powertrains is ≥ a minimum total instantaneous power required for the aircraft to continue its flight.

IPC Classes  ?

  • G09B 9/44 - Simulators for teaching or training purposes for teaching control of vehicles or other craft for teaching control of aircraft, e.g. Link trainer providing simulation in a real aircraft flying through the atmosphere without restriction of its path
  • G09B 9/46 - Simulators for teaching or training purposes for teaching control of vehicles or other craft for teaching control of aircraft, e.g. Link trainer the aircraft being a helicopter
  • B64C 27/12 - Rotor drives
  • G09B 9/08 - Simulators for teaching or training purposes for teaching control of vehicles or other craft for teaching control of aircraft, e.g. Link trainer

93.

Fuel supply circuit of an aircraft engine

      
Application Number 17759208
Grant Number 12006873
Status In Force
Filing Date 2021-01-15
First Publication Date 2023-03-02
Grant Date 2024-06-11
Owner SAFRAN HELICOPTER ENGINES (France)
Inventor
  • Dupeu, Franck Albert Robert
  • Gigon, Jean-Marie André Robert
  • Taieb, David Simon Serge

Abstract

A fuel supply circuit of an aircraft engine includes a centrifugal pump mechanically coupled with an engine shaft delivering mechanical power. The circuit further includes at least one electromagnetic pump including at least one stator delimiting an annular internal volume in which is present a rotor able to drive a fluid, a plurality of magnets annularly distributed on the rotor and at least a plurality of coils annularly distributed inside the stator face-to-face with the magnets. The rotor is connected to the engine shaft by a one-way clutching element.

IPC Classes  ?

  • F02C 7/236 - Fuel delivery systems comprising two or more pumps
  • F02C 7/26 - Starting; Ignition
  • F02C 9/30 - Control of fuel supply characterised by variable fuel pump output

94.

SENSOR FOR DETERMINING A LIQUID LEVEL FOR AN AIRCRAFT TANK, TANK-AND-SENSOR ASSEMBLY, METHOD FOR USING SUCH A SENSOR

      
Application Number EP2022071023
Publication Number 2023/020797
Status In Force
Filing Date 2022-07-27
Publication Date 2023-02-23
Owner SAFRAN HELICOPTER ENGINES (France)
Inventor
  • Moutaux, Antoine Pascal
  • Robert, Olivier

Abstract

The invention relates to a sensor (1) for determining a liquid level (NE) for an aircraft tank (100), the determining sensor (1) comprising a closure device (2) for closing a port (101) of the tank (100) and a measuring device (3), removably mounted on the closure device (2), comprising a liquid line (20) configured to convey liquid from the port (100) of the tank (100), and a member (21) for automatically sealing the liquid line (20) if the measuring device (3) is not mounted on the closure device (2), the measuring device (3) comprising at least one pressure measuring member (30) configured to measure a pressure difference between the liquid pressure (P1) in the liquid line (20) and a reference pressure (P2) in order to deduce the liquid level (NE) thereof.

IPC Classes  ?

  • G01F 23/16 - Indicating, recording, or alarm devices being actuated by mechanical or fluid means, e.g. using gas, mercury, or a diaphragm as transmitting element, or by a column of liquid
  • G01F 22/02 - Methods or apparatus for measuring volume of fluids or fluent solid material, not otherwise provided for involving measurement of pressure
  • G01F 23/00 - Indicating or measuring liquid level or level of fluent solid material, e.g. indicating in terms of volume or indicating by means of an alarm
  • F01M 11/12 - Indicating devices; Other safety devices concerning lubricant level

95.

Rotor blade for a turbomachine

      
Application Number 17760018
Grant Number 11852033
Status In Force
Filing Date 2021-02-04
First Publication Date 2023-02-23
Grant Date 2023-12-26
Owner SAFRAN HELICOPTER ENGINES (France)
Inventor
  • Bouchia, Youssef
  • Tarnowski, Laurent Pierre

Abstract

The invention relates to a rotor blade (10) for a turbomachine, in particular of an aircraft, comprising an airfoil (12) comprising a pressure face (15) and a suction face (17) extending from a leading edge (14) to a trailing edge (16), the airfoil (12) comprising an axis of elongation extending substantially along the leading (14) and trailing (16) edges, the airfoil (12) comprising a radially firmer end for connection to a rotor and a free radially outer end. According to the invention, the airfoil (10) further comprises at least one series of fins (24) situated on said free end, each of these fins (24) comprising a pressure face (26) situated on the suction face (17) side of the airfoil (12), and a suction face (28) situated on the pressure face (15) side of the airfoil (12).

IPC Classes  ?

  • F01D 5/20 - Specially-shaped blade tips to seal space between tips and stator
  • F01D 5/14 - Form or construction

96.

TURBOPROP CAPABLE OF PROVIDING AN EMERGENCY WIND-TURBINE FUNCTION AND AIRCRAFT COMPRISING SUCH A TURBOPROP

      
Application Number FR2022051548
Publication Number 2023/012435
Status In Force
Filing Date 2022-08-02
Publication Date 2023-02-09
Owner SAFRAN HELICOPTER ENGINES (France)
Inventor
  • Apostin, Lucie Stéphanie
  • Chartrain, Didier Claude
  • Presse, Jean-Michel

Abstract

The invention relates to a turboprop (10) comprising a propeller (12), a propeller shaft (13) carrying the propeller (12), the propeller being a variable-pitch propeller having a propeller pitch, a rotating electric machine (19) having at least a first configuration in which it is mechanically coupled to the propeller shaft (13) and at least one oil pump (21, 21B) configured to supply a hydraulic circuit for adjusting the pitch of the propeller (12). The oil pump is configured to be electrically operated. The invention further relates to an aircraft comprising such a turboprop (10) and to the methods for controlling such a turboprop (10) and such an aircraft.

IPC Classes  ?

  • F01D 15/10 - Adaptations for driving, or combinations with, electric generators
  • B64C 11/38 - Blade pitch-changing mechanisms fluid, e.g. hydraulic
  • F01D 25/20 - Lubricating arrangements using lubrication pumps
  • B64D 41/00 - Power installations for auxiliary purposes
  • B64D 27/02 - Aircraft characterised by the type or position of power plant
  • B64D 35/00 - Transmitting power from power plant to propellers or rotors; Arrangements of transmissions

97.

TURBOPROP CAPABLE OF PROVIDING AN EMERGENCY WIND-TURBINE FUNCTION AND AIRCRAFT COMPRISING SUCH A TURBOPROP

      
Document Number 03227356
Status Pending
Filing Date 2022-08-02
Open to Public Date 2023-02-09
Owner SAFRAN HELICOPTER ENGINES (France)
Inventor
  • Apostin, Lucie Stephanie
  • Chartrain, Didier Claude
  • Presse, Jean-Michel

Abstract

The invention relates to a turboprop (10) comprising a propeller (12), a propeller shaft (13) carrying the propeller (12), the propeller being a variable-pitch propeller having a propeller pitch, a rotating electric machine (19) having at least a first configuration in which it is mechanically coupled to the propeller shaft (13) and at least one oil pump (21, 21B) configured to supply a hydraulic circuit for adjusting the pitch of the propeller (12). The oil pump is configured to be electrically operated. The invention further relates to an aircraft comprising such a turboprop (10) and to the methods for controlling such a turboprop (10) and such an aircraft.

IPC Classes  ?

  • F01D 15/10 - Adaptations for driving, or combinations with, electric generators
  • B64C 11/38 - Blade pitch-changing mechanisms fluid, e.g. hydraulic
  • B64D 27/02 - Aircraft characterised by the type or position of power plant
  • F01D 25/20 - Lubricating arrangements using lubrication pumps

98.

TRANSFER OF POWER BETWEEN THE HIGH-PRESSURE SHAFT AND THE LOW-PRESSURE SHAFT OF A TURBOMACHINE

      
Document Number 03226595
Status Pending
Filing Date 2022-07-22
Open to Public Date 2023-02-02
Owner SAFRAN HELICOPTER ENGINES (France)
Inventor
  • Thiriet, Romain Jean Gilbert
  • Lemay, David Bernard Martin
  • Mercier-Calvairac, Fabien

Abstract

The invention relates to a device (136) for controlling a power-transfer system (124) for the transfer of power between a high-pressure shaft (108) and a low-pressure shaft (116) of a turbomachine (104) of an aircraft (102), comprising: - a fatigue analysis module (142) analysing the fatigue of the turbomachine (104) and designed to determine, from between two indicators (D1, D2) respectively measuring two fatigues of the turbomachine (104), which is the one that is the most advanced, which is to say which is the one at risk of being first to reach a respective upper limit (D1max, D2max); and - a control module (140) controlling the power transfer system (124) and designed to slow the fatigue measured by the more advanced indicator (D1, D2).

IPC Classes  ?

  • F02C 7/36 - Power transmission between the different shafts of the gas-turbine plant, or between the gas-turbine plant and the power user
  • F02C 3/113 - Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor with two or more rotors connected by power transmission with variable power transmission between rotors
  • F02C 9/28 - Regulating systems responsive to plant or ambient parameters, e.g. temperature, pressure, rotor speed
  • F02C 9/56 - Control of fuel supply conjointly with another control of the plant with power transmission control

99.

PROPELLER FOR AN AIRCRAFT PROPULSION ASSEMBLY, PROPULSION ASSEMBLY, AND METHOD FOR THE USE OF SUCH A PROPULSION ASSEMBLY

      
Application Number EP2022070058
Publication Number 2023/006473
Status In Force
Filing Date 2022-07-18
Publication Date 2023-02-02
Owner SAFRAN HELICOPTER ENGINES (France)
Inventor
  • Regaud, Pierre-Luc
  • Chartrain, Didier Claude
  • Combebias, Sébastien
  • Drouin, Thomas
  • Serghine, Camel
  • Tarnowski, Laurent Pierre
  • Derderian, Michael
  • Duqueine, Vincent

Abstract

A propeller (2) for an aircraft propulsion assembly (1) extending longitudinally along an axis X, the propeller (2) comprising a propeller cone (21), blades (22), a guide member (4) extending longitudinally along the axis X and rotating as one with the propeller cone (21), the guide member (4) being mounted outside the propeller cone (21) in such a way as to form between them a guide path (V), the guide member (4) having an upstream opening (41) configured to convey a flow of air in the guide path (V) and a downstream opening (42) in such a way as to remove the flow of air downstream, the guide member (4) having through-orifices (40) through which extend the blades (22) of the propeller (2) and compressor vanes (5), which rotate as one with with the propeller cone (21) and which are positioned in the guide path (V) in such a way as to generate an accelerated air flow.

IPC Classes  ?

  • B64C 11/14 - Spinners
  • B64C 11/02 - Hub construction
  • B64D 27/24 - Aircraft characterised by the type or position of power plant using steam, electricity, or spring force
  • B64D 33/08 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems

100.

TRANSFER OF POWER BETWEEN THE HIGH-PRESSURE SHAFT AND THE LOW-PRESSURE SHAFT OF A TURBOMACHINE

      
Application Number FR2022051469
Publication Number 2023/007076
Status In Force
Filing Date 2022-07-22
Publication Date 2023-02-02
Owner SAFRAN HELICOPTER ENGINES (France)
Inventor
  • Thiriet, Romain Jean Gilbert
  • Lemay, David Bernard Martin
  • Mercier-Calvairac, Fabien

Abstract

The invention relates to a device (136) for controlling a power-transfer system (124) for the transfer of power between a high-pressure shaft (108) and a low-pressure shaft (116) of a turbomachine (104) of an aircraft (102), comprising: - a fatigue analysis module (142) analysing the fatigue of the turbomachine (104) and designed to determine, from between two indicators (D1, D2) respectively measuring two fatigues of the turbomachine (104), which is the one that is the most advanced, which is to say which is the one at risk of being first to reach a respective upper limit (D1max, D2max); and - a control module (140) controlling the power transfer system (124) and designed to slow the fatigue measured by the more advanced indicator (D1, D2).

IPC Classes  ?

  • F02C 7/36 - Power transmission between the different shafts of the gas-turbine plant, or between the gas-turbine plant and the power user
  • F02C 9/28 - Regulating systems responsive to plant or ambient parameters, e.g. temperature, pressure, rotor speed
  • F02C 9/56 - Control of fuel supply conjointly with another control of the plant with power transmission control
  • F02C 3/113 - Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor with two or more rotors connected by power transmission with variable power transmission between rotors
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