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

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

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  ?

• G01M 15/00 - Testing of engines
• H02P 21/20 - Estimation of torque
• B64F 5/60 - Testing or inspecting aircraft components or systems
• G01R 31/34 - Testing dynamo-electric machines

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

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

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.

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  ?

• F02C 7/266 - Electric

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

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

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

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

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

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

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

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

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

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

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

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

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

Abstract

Device (30) for controlling an airflow guiding system (20), comprising at least one actuator (31) configured to translate a control rod (32) between a first and a second end position of a nominal operating range in which at least one vane (21a) of the airflow guiding system (20) can be moved between a first and a second angle, the control rod (32) being connected to the vane (21a) by a control lever (33) comprising a first control rod (36) and a second control rod (37) which are hinged together. The actuator (31) is configured to bring the control rod (32) into a safety position located beyond the second end position of the nominal operating range and to orient the vane (21a) 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

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

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

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

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

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

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

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  ?

• G06T 7/00 - Image analysis

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

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

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

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

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

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  ?

• F01D 25/32 - Collecting of condensation water; Drainage
• F01D 25/18 - Lubricating arrangements

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

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

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

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

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

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

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  ?

• F01D 25/18 - Lubricating arrangements
• F02C 7/06 - Arrangement of bearings; Lubricating
• F01D 25/12 - Cooling
• F16C 37/00 - Cooling of bearings

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

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

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

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

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  ?

• B01D 35/143 - Filter condition indicators

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

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

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

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

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

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

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 is 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

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

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

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

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  ?

• B64C 27/12 - Rotor drives

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

Abstract

A turbogenerator (1) for an aircraft (2) comprising: a turboshaft engine (3); an electric generator (4) comprising a rotor (5) driven mechanically by the turboshaft engine (3) and a stator (6) supported by a housing (7) of the electric generator (4); characterized in that the turbogenerator (1) comprises a static separator (8) for separating an air/oil mixture coming from the turboshaft engine (3), the static separator (8) being positioned around the housing (7) of the electric generator (4).

IPC Classes  ?

• F01D 25/18 - Lubricating arrangements
• F01D 15/10 - Adaptations for driving, or combinations with, electric generators
• 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 27/02 - Aircraft characterised by the type or position of power plant

Abstract

A method for manufacturing a blade with a first portion and a second portion, the method includes forming the first portion that includes forming a model of the first portion from removable material, forming a first shell mould from the model of the first portion, and forming the single-crystal or columnar first portion m a first metal alloy in the first shell mould from a single-crystal seed, and forming the second portion in which the second portion is formed on the first portion, and in which the first portion and the second portion are made from different materials, the second portion being polycrystalline and formed from a second metal alloy. The blade includes a single-crystal or columnar first portion made from a first metal alloy and a polycrystalline second portion made from the second metal alloy different from the first metal alloy.

IPC Classes  ?

• F01D 25/00 - Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
• F01D 9/02 - Nozzles; Nozzle boxes; Stator blades; Guide conduits
• B22D 27/04 - Influencing the temperature of the metal, e.g. by heating or cooling the mould
• C30B 29/52 - Alloys
• B33Y 10/00 - Processes of additive manufacturing
• B33Y 40/20 - Post-treatment, e.g. curing, coating or polishing
• 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
• B33Y 80/00 - Products made by additive manufacturing

Abstract

Rolling bearing with three contact points, wherein the inner raceway, the third contact point being located in a sector of the outer raceway delimited by a proximal end of the outer raceway on the one hand, and by the rolling plane on the other hand, characterized in that the outer ring comprises a drain provided in the outer raceway, and opening from an outer surface of the outer ring, said drain opening eccentrically on the outer raceway with respect to the rolling plane, in a sector of the outer raceway delimited by the rolling plane on the one hand, and a distal end of the outer raceway on the other hand, the drain and the third contact point being disjoint.

IPC Classes  ?

• F16C 33/66 - Special parts or details in view of lubrication
• F16C 19/16 - Bearings with rolling contact, for exclusively rotary movement with bearing balls essentially of the same size in one or more circular rows for both radial and axial load with a single row of balls

Abstract

The invention relates to a fire safety system (30) for a turbomachine (1), such as an aeroplane turbofan or a turboprop engine, the turbomachine comprising at least one turbine (3) having a turbine disc (5) and an annular cavity (16) which is arranged upstream of the disc (5), the disc (5) comprising an internal bore (7) and the fire safety system (30) comprising a cooling device (14) intended to supply the cavity (16) with cooling air via injection means (17). According to the invention, the fire safety system (30) comprises means configured such that, on the one hand, the annular cavity is divided into a first cavity and a second cavity and, on the other hand, a cooling air speed is maintained at the outlet of the injection means (16) and the cooling air in the first cavity is guided to the internal bore (7) of the turbine disc (5). Said means comprise a diffuser (52) co-operating with the injection means (17) and an annular cover intended to co-operate with the diffuser (52) and to cover first attachment members (27) arranged in the cavity (16), the diffuser (52) and the cover (40) being configured such that the cooling air at the outlet of the diffuser (52) is at least partially guided by a radially outer surface (40a) of the cover (40).

IPC Classes  ?

• F01D 5/08 - Heating, heat-insulating, or cooling means
• 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 25/12 - Cooling
• F01D 25/18 - Lubricating arrangements
• F02C 7/25 - Fire protection or prevention

Abstract

A device for supplying fuel to a combustion chamber of a gas generator includes an injection wheel (14) for injecting fuel into the combustion chamber (18),—a fuel supply rail (20) including an internal fuel circuit (30) with a fuel outlet means (32) supplying fuel to an annular spray chamber (24) formed between the rail (28, 44, 48, 52, 56) and the injection wheel (14),—at least one dynamic annular seal (26) adapted to provide a seal between an annular face (34) of the fuel supply rail (28, 44, 48, 52, 56) and the injection wheel (14), wherein the internal fuel circuit (30) of the fuel supply rail includes an annular fuel flow part arranged radially at the dynamic annular seal (26).

IPC Classes  ?

• F23R 3/38 - Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising rotary fuel injection means
• F02C 7/22 - Fuel supply systems
• F23R 3/28 - Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply

Abstract

A hybrid propulsion chain for an aircraft, the hybrid propulsion chain comprising a plurality of propulsion rotors connected to an electrical distribution module by a plurality of electrical connections, the electrical distribution module being connected, on the one hand, to a non-propulsion turbine engine via an electrical generation system and, on the other hand, to an electric battery, each propulsion rotor comprising a stator member and at least one rotor shaft which is configured to be rotated with respect to the stator member when the stator member is electrically powered, the hybrid propulsion chain comprising an auxiliary mechanical drive system mechanically connected to the non-propulsion turbine engine, the auxiliary mechanical drive system comprising a plurality of mechanical connections for mechanically rotating at least one rotor shaft of each propulsion rotor.

IPC Classes  ?

• B64D 27/24 - Aircraft characterised by the type or position of power plant using steam, electricity, or spring force
• B64D 35/04 - Transmitting power from power plant to propellers or rotors; Arrangements of transmissions characterised by the transmission driving a plurality of propellers or rotors
• H02K 7/18 - Structural association of electric generators with mechanical driving motors, e.g.with turbines

Abstract

A system (11) for balancing at least one parameter to be balanced of an electric motor of a propulsion system (1), in particular of an aircraft, includes at least two electric motors (3, 4) and a propulsion member (2) driven in rotation by said electric motors. The balancing system is configured to calculate a correction of the speed setpoint (Corr_Cons_VI, Corr_Cons_V2) as a function of a correction factor (F1, F2) of the speed setpoint depending on a parameter (P1, P2) of the associated electric motor that is intended to be balanced and on a speed setpoint (Cons_VH) of the propulsion member (2).

IPC Classes  ?

• B64D 31/12 - Initiating means actuated automatically for equalising or synchronising power plants
• H02P 5/50 - Arrangements specially adapted for regulating or controlling the speed or torque of two or more electric motors for speed regulation of two or more dynamo-electric motors in relation to one another by comparing electrical values representing the speeds
• 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

Abstract

The invention relates to a system (100) which comprises: a gas turbine (102) designed so that a combustion chamber (110) can be ignited in a first ignition range of rotational speeds of a compressor shaft (112); and a control device (106) designed to control an electric starter (114) to accelerate the compressor shaft (112), and, when the compressor shaft (112) is accelerated, to control an attempt to ignite the combustion chamber (110). The gas turbine (102) is designed so that the combustion chamber (110) can be ignited in a second ignition range which is higher than the first ignition range, but not between these two ignition ranges, and the ignition attempt is carried out in the second ignition range.

IPC Classes  ?

• F02C 7/26 - Starting; Ignition
• F02C 7/262 - Restarting after flame-out
• F02C 7/268 - Starting drives for the rotor

Abstract

A rotor wheel (10) for an aircraft turbine engine, said wheel comprising: - a disc (12) having a main axis (A) and provided with cells (14) at its outer periphery, the cells extending along the axis and each comprising a bottom (14a) and two side flanks (14b), - vanes (22) mounted in the cells (14) of the disc (12), each of said vanes comprising a blade (24) connected by a platform (26) to a root (28) which is configured to be interlockingly mounted in one of the cells (14), the root (28) of each of the vanes (22) comprising, at its radially inner end, a lobe (30) with a first axial end which comprises a circumferential notch (32) and a second axial end, opposite the first end, which comprises a radially inward facing stop (33) configured to axially bear on a first face (12b) of the disc (12), and - a split annular ring (34) engaged in the notches (32) of the vanes (22) and axially clamped against a second face (12a) of the disc, the second face (12a) being opposite the first face (12b), the lobe (30) of the root (28) of each of the vanes (22) comprising, between the first and second ends, a radially inward facing projecting bulb (42) configured to radially bear on the surface of the bottom (14a) of the corresponding cell (14).

IPC Classes  ?

• F01D 5/30 - Fixing blades to rotors; Blade roots
• F01D 5/32 - Locking, e.g. by final locking-blades or keys
• F01D 11/00 - Preventing or minimising internal leakage of working fluid, e.g. between stages

Abstract

A propulsion system (1) for a helicopter, comprising a turboshaft engine (2) with a linked turbine and an electric machine (3) capable of operating as an electric motor, the turboshaft engine (2) and the electric machine (3) being capable of driving in rotation at least one main rotor (5) intended to be coupled to a rotating wing (6) characterised in that it comprises means of coupling and decoupling (14) in rotation between a rotor (3a) of the electric machine (3) and a rotor (2a) of the turboshaft engine (2), the means of coupling and decoupling (14) being capable of allowing the rotor (2a) of the turboshaft engine (2) to be driven in rotation with the aid of the electric machine (3), in a first state of the propulsion system (1), and capable of allowing the rotor (2a) of the turboshaft engine (2) and the rotor (3a) of the electric machine (3) to be decoupled in rotation, in a second state of the propulsion system (1).

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
• B64C 27/12 - Rotor drives
• B64D 27/24 - Aircraft characterised by the type or position of power plant using steam, electricity, or spring force

Abstract

The invention relates to a turbomachine comprising a rotary body comprising a motor shaft supplying mechanical power, and at least one magnetic drive pump comprising at least: one stator (110) delimiting an annular inner space and comprising a first and a second flange (1110, 1120), a rotor (120) 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), a pair of magnets (1241, 1242) having opposite polarities coaxially arranged on the rotor with the axis of rotation, a magnet (1116) arranged on the first flange (1110) in order to co-operate with one of the magnets of the pair of magnets of the rotor, a magnetic means (130) for rotating the rotor arranged on the second flange (1120), the second flange being non-magnetic.

IPC Classes  ?

• F02C 7/22 - Fuel supply systems
• F04D 29/048 - Bearings electromagnetic

Abstract

A device (110) for guiding a main air flow (F1) for an aircraft turbine engine (22), said device comprising: a first air flowing pipe (112) of a main air flow (F1), said first pipe having a main axis (A), - a plurality of ejectors (114) of a secondary air flow (F2) located within the first pipe (112) and configured to eject a secondary air flow (F2) and force the flow of the main air flow (F1) into said first pipe (112), the ejectors (114) being distributed around the main axis (A), and - a second air flowing pipe (116) located at the outlet of the ejectors (114) and comprising one end (116a) which is connected to one end (112a) of the first pipe (112), characterised in that the second pipe (116) comprises a narrow end (134).

IPC Classes  ?

• F02C 7/052 - Air intakes for gas-turbine plants or jet-propulsion plants having provisions for obviating the penetration of damaging objects or particles with dust-separation devices
• F04F 5/16 - Jet pumps, i.e. devices in which fluid flow is induced by pressure drop caused by velocity of another fluid flow the inducing fluid being elastic fluid displacing elastic fluids
• F04F 5/46 - Arrangements of nozzles

Abstract

A turbomachine comprises a rotating spool comprising a drive shaft delivering mechanical power. The turbomachine comprises an electromagnetic pump mechanically decoupled from the drive shaft. The electromagnetic pump comprises at least one stator delimiting an annular internal volume in which is present a rotor able to drive a fluid, a plurality of magnets distributed annularly on the rotor and at least one plurality of coils distributed annularly inside the rotor. The coils of the plurality of coils face magnets along an axial direction.

IPC Classes  ?

• F04C 2/10 - Rotary-piston machines or pumps of intermeshing-engagement type, i.e. with engagement of co-operating members similar to that of toothed gearing of internal-axis type with the outer member having more teeth or tooth-equivalents, e.g. rollers, than the inner member
• F04C 15/00 - Component parts, details or accessories of machines, pumps or pumping installations, not provided for in groups
• F04C 7/00 - Rotary-piston machines or pumps with fluid ring or the like
• F02C 7/32 - Arrangement, mounting, or driving, of auxiliaries

Abstract

A device (110) for guiding a main air flow (F1) for an aircraft turbine engine (22), said device comprising: a first air flowing pipe (112) of a main air flow (F1), said first pipe having a main axis (A), - a plurality of ejectors (114) of a secondary air flow (F2) located within the first pipe (112) and configured to eject a secondary air flow (F2) and force the flow of the main air flow (F1) into said first pipe (112), the ejectors (114) being distributed around the main axis (A), and - a second air flowing pipe (116) located at the outlet of the ejectors (114) and comprising one end (116a) which is connected to one end (112a) of the first pipe (112), characterised in that the second pipe (116) comprises a narrow end (134).

IPC Classes  ?

• F02C 7/052 - Air intakes for gas-turbine plants or jet-propulsion plants having provisions for obviating the penetration of damaging objects or particles with dust-separation devices
• F04F 5/16 - Jet pumps, i.e. devices in which fluid flow is induced by pressure drop caused by velocity of another fluid flow the inducing fluid being elastic fluid displacing elastic fluids
• F04F 5/46 - Arrangements of nozzles

Abstract

The invention relates to a transmission device (1) for hybrid aircraft comprising a turboshaft engine having a gas generator (12), a free turbine (14), and a main rotor (52), the device comprising a first reversible electric motor (30) coupled to a shaft (16) of the free turbine (14) via a first disengageable coupling means (32), and to the main rotor (52), and a second reversible electric motor (40) coupled to a shaft (18) of the gas generator (12) via a second disengageable coupling means (44), and coupled to the main rotor (52) via a third disengageable coupling means (42), the second disengageable coupling means (44) being operable when the second electric motor (40) rotates in a first direction of rotation, and the third disengageable coupling means (42) being operable when the second electric motor (40) rotates in a second direction of rotation opposite to the first direction of rotation.

IPC Classes  ?

• B64D 27/10 - Aircraft characterised by the type or position of power plant of gas-turbine type
• B60K 6/50 - Architecture of the driveline characterised by arrangement or kind of transmission units
• F01D 15/10 - Adaptations for driving, or combinations with, electric generators
• F02C 7/32 - Arrangement, mounting, or driving, of auxiliaries
• B64D 35/02 - Transmitting power from power plant to propellers or rotors; Arrangements of transmissions characterised by the type of power plant
• 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

Abstract

The system comprises: - a fuel tank; - a suction pipe that is connected to the tank and is located higher than the tank; - an electric pump (36); - a supply pump configured to be mechanically driven by an accessory gear box and be connected, at the outlet, to a fuel supply circuit for the engine; and - an air evacuation drain (26). The electric pump (36) is in communication with the suction pipe independently of the supply pump, and with the drain. The supply pump is in communication with the suction pipe independently of the electric pump.

IPC Classes  ?

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