SAFRAN S.A.

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IPC Class
F01D 5/28 - Selecting particular materials; Measures against erosion or corrosion 53
C22C 19/05 - Alloys based on nickel or cobalt based on nickel with chromium 23
B64D 27/24 - Aircraft characterised by the type or position of power plant using steam, electricity, or spring force 20
D03D 25/00 - Woven fabrics not otherwise provided for 20
B29C 70/24 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements using fibres of substantial or continuous length oriented in at least three directions forming a three dimensional structure 19
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1.

NICKEL-BASED SUPERALLOY, SINGLE-CRYSTAL BLADE AND TURBOMACHINE

      
Application Number 18553416
Status Pending
Filing Date 2022-03-25
First Publication Date 2024-06-13
Owner SAFRAN (France)
Inventor
  • Rame, Jérémy
  • Menou, Edern

Abstract

A nickel-based superalloy including, in weight percentages, 5.5 to 7.5% of aluminum, 1.0 to 4.0% of tantalum, 0.50 to 3.0% of titanium, 3.0 to 7.0% of cobalt, 8.0 to 12.0% of chromium, 0 to 2.5% of molybdenum, 0 to 3.0% of tungsten, 0.50 to 2.8% of rhenium, 0.05 to 0.25% of hafnium, 0 to 0.15% of silicon, the remainder consisting of nickel and unavoidable impurities.

IPC Classes  ?

  • F01D 5/28 - Selecting particular materials; Measures against erosion or corrosion
  • C22C 19/05 - Alloys based on nickel or cobalt based on nickel with chromium
  • C30B 29/52 - Alloys

2.

CONFIGURABLE POWER SUPPLY SYSTEM

      
Application Number 18285793
Status Pending
Filing Date 2022-04-08
First Publication Date 2024-06-13
Owner SAFRAN (France)
Inventor
  • Abdellatif, Meriem
  • Pauvert, Vincent
  • Meunier, René

Abstract

A power supply system comprising: a first converter module comprising an AC/DC converter and being arranged to produce an intermediate voltage from an input voltage; a second converter module comprising a DC/DC converter and being controllable to use the intermediate voltage to produce selectively at least two distinct output voltage levels; and a control unit arranged to acquire a flight parameter representative of the flight phase and/or of the altitude, and to control the power supply system in such a manner that the second converter module delivers to each electrical system a power supply voltage that depends on the flight parameter and on said electrical system, and that is equal to one of the output voltage levels.

IPC Classes  ?

  • H02J 3/46 - Controlling the sharing of output between the generators, converters, or transformers
  • B64C 25/32 - Alighting gear characterised by elements which contact the ground or similar surface
  • B64D 13/06 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned
  • H02J 1/10 - Parallel operation of dc sources
  • H02J 3/38 - Arrangements for parallelly feeding a single network by two or more generators, converters or transformers

3.

METHOD, DEVICE AND COMPUTER PROGRAM FOR ESTIMATING A SPEED OF A WHEELED VEHICLE

      
Application Number 18281137
Status Pending
Filing Date 2022-03-09
First Publication Date 2024-05-30
Owner
  • SAFRAN (France)
  • INSTITUT NATIONAL DE RECHERCHE EN INFORMATIQUE ET EN AUTOMATIQUE (France)
Inventor
  • Abboud, Dany
  • Barrau, Axel
  • Leiber, Maxime
  • Marnissi, Yosra

Abstract

The present invention relates to a method for estimating a speed (v) of movement of a wheeled vehicle, wherein a frequency trajectory (ξt) representative of the speed (v) of a wheel (RO) of the vehicle (VE) in a filtered spectrogram (S(ft, t)) is estimated (E5) as follows: a probability (pZt|ξt) of observation of the trajectory (ft) is estimated (E51) on the basis of a computed amplitude of the filtered spectrogram (S(ft, t)), an a posteriori observation law (pZt|ξt) proportional to the product of the probability (pξ) and of the probability (pξ|Z)′ is estimated (E52), the trajectory (ft) is estimated (E53) on the basis of the law (pξ|Z), and the speed (v) of movement of the wheel of the vehicle is estimated (E6) on the basis of the trajectory (ξt).

IPC Classes  ?

  • G01P 3/48 - Devices characterised by the use of electric or magnetic means for measuring angular speed by measuring frequency of generated current or voltage
  • G01H 1/10 - Measuring vibrations in solids by using direct conduction to the detector of torsional vibrations
  • G01N 29/46 - Processing the detected response signal by spectral analysis, e.g. Fourier analysis
  • G01P 3/50 - Devices characterised by the use of electric or magnetic means for measuring linear speed

4.

TIAL INTERMETALLIC CASTING ALLOY

      
Application Number 18552348
Status Pending
Filing Date 2022-03-23
First Publication Date 2024-05-23
Owner
  • SAFRAN (France)
  • OFFICE NATIONAL D'ETUDES ET DE RECHERCHES AEROSPATIALES (France)
Inventor
  • Sallot, Pierre Jean
  • Huvelin, Zhao
  • Perrut, Mikael
  • Bachelier-Locq, Agnès

Abstract

The present disclosure relates to the technical field of TiAl intermetallic foundry alloys. More particularly, it relates to such an alloy comprising: 44≤Al≤47 at. %; 0

IPC Classes  ?

  • C22F 1/18 - High-melting or refractory metals or alloys based thereon
  • C22C 14/00 - Alloys based on titanium
  • C22F 1/00 - Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working

5.

METHOD FOR MANUFACTURING A TURBOMACHINE COMPONENT MADE OF COMPOSITE MATERIAL WITH A STIFFENING ZONE

      
Application Number 18550063
Status Pending
Filing Date 2022-03-16
First Publication Date 2024-05-16
Owner SAFRAN (France)
Inventor
  • Charleux, François
  • Colot, Marc-Antoine

Abstract

A method for manufacturing a turbomachine component made of composite material includes the step of creating a shaped fibrous preform by three-dimensional weaving of filaments to create a fibrous texture which is wound in several superposed layers onto a mandrel of a profile corresponding to that of the component that is to be manufactured, so as to obtain the fibrous preform of a shape corresponding to that of the component that is to be manufactured, the filaments being divided into warp filaments and weft filaments, the warp filaments being interwoven with the weft filaments in a three-dimensional weave. The method further includes the step of creating a stiffening zone in the fibrous preform, the stiffening zone being formed of at least one layer of warp filaments not interwoven with weft filaments that is interposed between the interwoven warp filaments and weft filaments.

IPC Classes  ?

  • F01D 25/00 - Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
  • B29C 70/24 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements using fibres of substantial or continuous length oriented in at least three directions forming a three dimensional structure
  • B29K 105/08 - Condition, form or state of moulded material containing reinforcements, fillers or inserts of continuous length, e.g. cords, rovings, mats, fabrics, strands or yarns
  • B29L 31/00 - Other particular articles
  • B32B 5/02 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by structural features of a layer comprising fibres or filaments
  • B32B 5/12 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by structural features of a layer comprising fibres or filaments characterised by the relative arrangement of fibres or filaments of adjacent layers
  • B32B 5/26 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by the presence of two or more layers which comprise fibres, filaments, granules, or powder, or are foamed or specifically porous one layer being a fibrous or filamentary layer another layer also being fibrous or filamentary
  • D03D 25/00 - Woven fabrics not otherwise provided for

6.

METHOD FOR ASSISTING WITH THE NAVIGATION OF A VEHICLE

      
Application Number 18281395
Status Pending
Filing Date 2022-03-11
First Publication Date 2024-05-16
Owner SAFRAN (France)
Inventor Barrau, Axel

Abstract

Method, navigation device and computer program product for assisting with the navigation of a vehicle equipped with a navigation device, comprising the following steps: acquiring (201) a priori values of kinematic variables of the navigation device, determining (202) respective current values of kinematic variables of the navigation device and a current uncertainty matrix representative of an uncertainty of the respective current values of the kinematic variables, based on respective previous values of the kinematic variables, determining (203) a correction, updating (204) the respective current values of the kinematic variables based on the correction and on the current uncertainty matrix.

IPC Classes  ?

  • G01C 21/16 - Navigation; Navigational instruments not provided for in groups by using measurement of speed or acceleration executed aboard the object being navigated; Dead reckoning by integrating acceleration or speed, i.e. inertial navigation

7.

METHOD FOR ASSISTING WITH THE NAVIGATION OF A VEHICLE

      
Application Number 18281446
Status Pending
Filing Date 2022-03-11
First Publication Date 2024-05-16
Owner SAFRAN (France)
Inventor Barrau, Axel

Abstract

Method, navigation device and computer program product for assisting with the navigation of a vehicle equipped with a navigation device, comprising the following steps: acquiring a priori values of kinematic variables of the navigation device, determining (202) respective current values of the kinematic variables of the navigation device and a current uncertainty matrix representative of an uncertainty of the respective current values of the kinematic variables, based on respective previous values of the kinematic variables, a previous uncertainty matrix representative of an uncertainty of the respective previous values of the kinematic variables and a model of Earth's gravity experienced by the navigation device, the modeled gravity increasing with an altitude of the navigation device.

IPC Classes  ?

  • G01C 21/16 - Navigation; Navigational instruments not provided for in groups by using measurement of speed or acceleration executed aboard the object being navigated; Dead reckoning by integrating acceleration or speed, i.e. inertial navigation

8.

LASER SHOCK METHOD

      
Application Number 18282176
Status Pending
Filing Date 2022-02-23
First Publication Date 2024-05-16
Owner
  • SAFRAN (France)
  • CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE (France)
  • SORBONNE UNIVERSITE (France)
  • ECOLE NATIONALE SUPERIEURE D'ARTS ET METIERS (ENSAM) (France)
  • CONSERVATOIRE NATIONAL DES ARTS ET METIERS (France)
Inventor
  • Ducousso, Mathieu Loïc
  • Cuenca, Edouardo
  • Coulouvrat, François
  • Berthe, Laurent

Abstract

A method for focusing acoustic waves on an interface between two layers of a multilayer structure includes providing laser means able to emit a laser beam toward an exterior surface of the multilayer structure to produce a longitudinal wave from the centre of a laser-beam spot projected onto the exterior surface and a transverse wave from the periphery of said spot, determining the distance between said interface and the exterior surface, determining one or more propagation velocities of each of the longitudinal wave and the transverse wave in the one or more layers passed through by said waves to reach said interface, and determining a radius of the laser-beam spot depending on the one or more propagation velocities and on said distance so that the time taken by the longitudinal wave to reach said interface is equal to three times the time taken by the transverse wave to reach said interface.

IPC Classes  ?

  • G01N 21/17 - Systems in which incident light is modified in accordance with the properties of the material investigated

9.

SURFACE HEAT EXCHANGER HAVING ADDITIONAL OUTLETS

      
Application Number 18548780
Status Pending
Filing Date 2022-03-06
First Publication Date 2024-05-09
Owner SAFRAN (France)
Inventor
  • Toubiana, Ephraïm
  • Maalouf, Samer
  • Holka, Quentin

Abstract

A surface heat exchanger for an aircraft turbomachine includes a support wall, a panel parallel to the support wall, partitions connecting the wall to the panel to define channels in which an air flow flows, and fins situated in the channels. The panel has a central part parallel to the wall and a downstream part that is inclined with respect to the wall. An upstream end is connected to the central part and a downstream end is situated at a distance from the wall and delimits with the latter a main outlet of the channels. The downstream part has fixed flaps disposed one after another so as to delimit between one another additional outlets of the channels.

IPC Classes  ?

  • F28D 1/053 - Heat-exchange apparatus having stationary conduit assemblies for one heat-exchange medium only, the media being in contact with different sides of the conduit wall, in which the other heat-exchange medium is a large body of fluid, e.g. domestic or mo with the heat-exchange conduits immersed in the body of fluid with tubular conduits the conduits being straight
  • F28F 1/32 - Tubular elements or assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with projections, with recesses the means being only outside the tubular element and extending transversely the means having portions engaging further tubular elements

10.

METHOD FOR THREE-DIMENSIONAL OR MULTILAYER WEAVING OF A FIBROUS STRUCTURE AND FIBROUS STRUCTURE HAVING A THREE-DIMENSIONAL OR MULTILAYER WEAVE

      
Application Number 18547543
Status Pending
Filing Date 2022-02-24
First Publication Date 2024-04-25
Owner SAFRAN (France)
Inventor
  • Coupe, Dominique Marie Christian
  • Kribs, Célline
  • Retiveau-Leca, Adrienne

Abstract

A fibrous structure intended to form the fibrous reinforcement of a part made of composite material includes a fibrous reinforcement densified by a matrix, the fibrous structure having a three-dimensional or multilayer weave between a plurality of layers of warp yarns and a plurality of layers of weft yarns. The fibrous structure includes at least a first portion having a first type of weave and a second portion, continuing on from the first portion, having a second type of weave, the warp yarns and the weft yarns having a degree of interweaving in the first type of weave that is greater than the degree of interweaving of the warp yarns and the weft yarns in the second type of weave.

IPC Classes  ?

  • D03D 1/00 - Woven fabrics designed to make specified articles
  • D03D 13/00 - Woven fabrics characterised by the special disposition of the warp or weft threads, e.g. with curved weft threads, with discontinuous warp threads, with diagonal warp or weft
  • D03D 25/00 - Woven fabrics not otherwise provided for

11.

DISTRIBUTED PROPULSION WITH OFFSET PROPULSION MODULES

      
Application Number 17769554
Status Pending
Filing Date 2020-10-13
First Publication Date 2024-04-25
Owner
  • INSTITUT SUPERIEUR DE L'AERONAUTIQUE ET DE L'ESPAC (France)
  • SAFRAN (France)
  • SAFRAN AIRCRAFT ENGINES (France)
Inventor
  • Gonidec, Patrick
  • Aguirre, Miguel Angel
  • Duplaa, Sébastien
  • Robic, Bernard
  • Rodriguez, Benoit
  • Tantot, Nicolas Jérôme Jean

Abstract

A propulsion unit including: a gas generator including a compressor, a combustion chamber, a turbine, at least two compressed-air propulsion modules, each propulsion module including: a fan, a compressed-air turbine configured to drive the rotation of the fan, a manifold allowing the respective turbines of the compressed-air propulsion modules to be supplied with compressed air, wherein the manifold is configured to collect and mix: at least a portion of the flow that has passed through the combustion chamber of the gas generator, typically as it leaves the turbine, and at least one bypass flow, the bypass flow being a flow of air which is not passed through the combustion chamber of the gas generator.

IPC Classes  ?

  • F02C 3/04 - Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
  • B64D 27/10 - Aircraft characterised by the type or position of power plant of gas-turbine type
  • F04D 17/02 - Radial-flow pumps specially adapted for elastic fluids, e.g. centrifugal pumps; Helico-centrifugal pumps specially adapted for elastic fluids having non-centrifugal stages, e.g. centripetal

12.

FIBROUS TEXTURE FOR A THIN-EDGED COMPOSITE BLADE

      
Application Number 18546902
Status Pending
Filing Date 2022-03-01
First Publication Date 2024-04-25
Owner SAFRAN (France)
Inventor
  • Coupe, Dominique Marie Christian
  • Colot, Marc-Antoine

Abstract

A fibrous texture for a blade has a three-dimensional weave between a first plurality of yarn layers and a second plurality of yarn layers, includes a blade aerofoil part extending between a first edge and a second edge. The texture includes a first part with at least three yarn layers of the first plurality of yarns and at least three yarn layers of the second plurality of yarns. Yarns of the two yarn layers of the first plurality of yarns bind yarns of the second plurality of yarns to the two yarn layers of the second plurality of yarns with a determined binding frequency.

IPC Classes  ?

  • D03D 25/00 - Woven fabrics not otherwise provided for
  • B29C 70/24 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements using fibres of substantial or continuous length oriented in at least three directions forming a three dimensional structure

13.

TURBOJET WITH IMPROVED AIR EXTRACTION PERFORMANCE

      
Application Number 18249417
Status Pending
Filing Date 2021-10-19
First Publication Date 2024-04-04
Owner SAFRAN (France)
Inventor
  • Parmentier, Nicolas Claude
  • Riera, William Henri Joseph

Abstract

A turbojet includes in succession, from upstream to downstream in the flow direction of a primary air stream: a low-pressure casing, an intermediate casing, and a high-pressure casing that are longitudinally aligned and which jointly delimit an internal annular passage for the circulation of the air stream. The intermediate casing delimits a portion of the annular passage called a gooseneck and includes: an air discharge system able to extract air from the air stream circulating in a first zone of the gooseneck and to discharge it outside the passage, and an air extraction system able to extract air circulating in a second zone of the gooseneck for an air conditioning system, the second air extraction zone being located downstream of the first air extraction zone.

IPC Classes  ?

  • 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

14.

METHOD FOR MANUFACTURING A HOLLOW PART

      
Application Number 17753579
Status Pending
Filing Date 2020-09-11
First Publication Date 2024-03-28
Owner SAFRAN (France)
Inventor
  • Obert, Enrico Giovanni
  • Touze, Adrien

Abstract

The invention relates to a method for manufacturing a hollow part made of composite material for an aircraft turbomachine, wherein: a) a preform is produced by the three-dimensional weaving of threads; b) the preform is cut so as to provide a separation; c) the cut preform is deformed so as to provide an orifice then comprising a first and a second open end (27a, 27b); d) the deformed preform is placed into an injection mould; e) a resin is injected in order to impregnate the whole of the deformed preform; f) the resin is polymerised; and g) a composite part is extracted from the mould; characterised in that: h) a flexible mandrel (31) with a predetermined shape is positioned in the orifice before the injection step e); i) the flexible mandrel (31) is removed after step f) or the demoulding step g), the composite part then having a hollow core (25).

IPC Classes  ?

  • F01D 5/18 - Hollow blades; Heating, heat-insulating, or cooling means on blades
  • B29C 37/00 - Component parts, details, accessories or auxiliary operations, not covered by group or
  • B29C 70/24 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements using fibres of substantial or continuous length oriented in at least three directions forming a three dimensional structure
  • B29C 70/48 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs and impregnating the reinforcements in the closed mould, e.g. resin transfer moulding [RTM]

15.

PROTECTION FOR THE COILS OF AN ELECTRIC MACHINE

      
Application Number 18273428
Status Pending
Filing Date 2022-01-18
First Publication Date 2024-03-21
Owner
  • SAFRAN (France)
  • UNIVERSITE DE LORRAINE (France)
Inventor
  • Ayat, Sabrina Siham
  • Dorget, Rémi Luc Stéphane
  • Daguse, Benjamin

Abstract

This invention relates to a superconducting electric machine (1), for example with axial flux or with radial flux, comprising an inductor (3) comprising superconducting pellets (7) circumferentially distributed around an axis (X) of the electric machine (1) and a flux barrier (12) comprising a superconducting material, said flux barrier (12) being centered on the axis (X) of rotation and extending radially inward of the superconducting pellets (7).

IPC Classes  ?

  • H02K 55/00 - Dynamo-electric machines having windings operating at cryogenic temperatures
  • B64D 27/24 - Aircraft characterised by the type or position of power plant using steam, electricity, or spring force
  • H01F 6/00 - Superconducting magnets; Superconducting coils

16.

PROTECTION FOR THE COILS OF AN ELECTRIC MACHINE

      
Application Number 18273488
Status Pending
Filing Date 2022-01-13
First Publication Date 2024-03-21
Owner
  • SAFRAN (France)
  • UNIVERSITE DE LORRAINE (France)
Inventor
  • Ayat, Sabrina Siham
  • Dorget, Rémi Luc Stéphane
  • Daguse, Benjamin

Abstract

The present invention relates to a superconducting electric machine (1) comprising an inductor (3) having: —superconducting pellets (7) circumferentially distributed about an axis (X) of the electric machine (1), —an armature (2) comprising coils (5), each coil (5) having a circumferential radially inner edge (10) and a circumferential radially outer edge (9), and—at least one flow barrier (12, 12′) extending circumferentially with respect to the axis (X), each flow barrier (12) extending between the superconducting pellets (7) and the armature (2) so as to at least partially cover at least one of the radially outer edge (9) and the radially inner edge (10) of all or part of the coils (5) of the armature (2).

IPC Classes  ?

  • H02K 55/02 - Dynamo-electric machines having windings operating at cryogenic temperatures of the synchronous type
  • B64D 27/24 - Aircraft characterised by the type or position of power plant using steam, electricity, or spring force

17.

AIRCRAFT PART MADE OF SUPERALLOY COMPRISING RHENIUM AND/OR RUTHENIUM AND ASSOCIATED MANUFACTURING METHOD

      
Application Number 17766764
Status Pending
Filing Date 2020-10-08
First Publication Date 2024-03-21
Owner SAFRAN (France)
Inventor
  • Saboundji, Amar
  • Crabos, Fabrice

Abstract

The present invention relates to a method for manufacturing a part, comprising the steps of chemically etching, in a wet acid medium, at least a portion of a surface of a substrate made of a monocrystalline superalloy, comprising at least one element chosen from rhenium and ruthenium, the substrate having a γ-γ′ phase, the substrate having an average mass fraction of rhenium and/or ruthenium greater than or equal to 3%, the chemical etching being done in such a way that the average mass fraction of rhenium and/or ruthenium over the portion of the surface of the substance is less than 2%, and a step of depositing on the portion of the substrate a protective coating having a γ-γ′ phase and an average mass fraction of rhenium and/or ruthenium of less than 1%.

IPC Classes  ?

  • C23C 14/02 - Pretreatment of the material to be coated
  • B32B 15/01 - Layered products essentially comprising metal all layers being exclusively metallic
  • C22C 19/05 - Alloys based on nickel or cobalt based on nickel with chromium
  • C23C 14/16 - Metallic material, boron or silicon on metallic substrates or on substrates of boron or silicon

18.

METHOD FOR OBTAINING A PRODUCT MADE OF TITANIUM ALLOY OR A TITANIUM-ALUMINIUM INTERMETALLIC COMPOUND

      
Application Number 18254966
Status Pending
Filing Date 2021-12-02
First Publication Date 2024-03-21
Owner SAFRAN (France)
Inventor Sallot, Pierre Jean

Abstract

A method for obtaining a product made of titanium alloy or a titanium-aluminum intermetallic compound by plasma torch melting, the alloy having an oriented structure, the method including heating the molten alloy surface in a casting ring with a plasma torch; cooling a cold zone of the casting ring over a length L1, the cooling forming a semi-solid crown of alloy; heating a hot zone of the casting ring over a length L2, thereby forming a solidification front, the flatness of which relative to a plane perpendicular to a drawing direction is less than 10°; and drawing the solidified alloy at a speed of more than 10−4 m/s in the drawing direction. The present disclosure also relates to a plant having one or more devices for implementing the method.

IPC Classes  ?

  • B22D 41/015 - Heating means with external heating, i.e. the heat source not being a part of the ladle
  • B22D 11/00 - Continuous casting of metals, i.e. casting in indefinite lengths
  • B22D 11/041 - Continuous casting of metals, i.e. casting in indefinite lengths into open-ended moulds for vertical casting
  • B22D 11/112 - Treating the molten metal by accelerated cooling
  • B22D 11/14 - Plants for continuous casting, e.g. for upwardly drawing the strand
  • B22D 21/00 - Casting non-ferrous metals or metallic compounds so far as their metallurgical properties are of importance for the casting procedure; Selection of compositions therefor
  • B22D 27/04 - Influencing the temperature of the metal, e.g. by heating or cooling the mould
  • C22C 1/02 - Making non-ferrous alloys by melting
  • C22C 14/00 - Alloys based on titanium

19.

METHOD FOR MONITORING THE STATE OF MECHANICAL COMPONENTS ON A SHAFT LINE, ASSOCIATED MONITORING DEVICE AND SYSTEM

      
Application Number 18262454
Status Pending
Filing Date 2022-01-19
First Publication Date 2024-03-21
Owner SAFRAN (France)
Inventor
  • Assoumane, Amadou
  • Abboud, Dany
  • El Badaoui, Mohammed

Abstract

The invention relates to a method for monitoring the state of mechanical components such as bearings and gears on a shaft line equipping a rotating machine. Said method includes a step of obtaining at least one measurement yc[k] of the absolute acceleration of the shaft, as well as a set of steps of: obtaining a value fr[k] of the rotational frequency of the shaft, determining a matrix H[k] making it possible to define a state model described by: [k+1]=x[k]+w[k]etY[k]=[(y_c [k])¦SE[k]]=H[k]×x[k]+v[k], determining an estimator of the vector x[k] based on data from the state model, said set of steps further including, for at least one mechanical component, steps of: determining, from said estimator, a quantity characteristic of a contribution of said component to the vector Y[k], comparing said quantity with a threshold, detecting a possible defect of said at least one mechanical component.

IPC Classes  ?

  • G01M 13/045 - Acoustic or vibration analysis
  • G01M 15/14 - Testing gas-turbine engines or jet-propulsion engines

20.

PROPULSION SYSTEM FOR AN AIRCRAFT

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

Abstract

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

IPC Classes  ?

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

21.

SYSTEM FOR CONTROLLING DISCHARGE DOORS OF A TURBOMACHINE

      
Application Number 18263624
Status Pending
Filing Date 2022-01-26
First Publication Date 2024-03-14
Owner SAFRAN (France)
Inventor
  • Parmentier, Nicolas Claude
  • Perez, Gabriel

Abstract

A system for controlling discharge doors of a turbomachine includes: a ring and a device connecting the ring to each discharge door. The ring is made up of bars connected end-to-end by rotary links ensuring that a bar pivoting on itself causes the other bars to pivot on themselves, with each discharge door being connected to a corresponding bar in order to open or close when this bar pivots

IPC Classes  ?

  • F01D 17/10 - Final actuators
  • 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

22.

METHOD AND DEVICE FOR CHECKING THE COMPLIANCE OF A WORKPIECE

      
Application Number 17754585
Status Pending
Filing Date 2020-10-07
First Publication Date 2024-03-07
Owner
  • SAFRAN AIRCRAFT ENGINES (France)
  • SAFRAN (France)
Inventor
  • Descoqs, Augustin Marie Michel
  • Ricordeau, Julien Alexis Louis
  • Sulli, Quentin

Abstract

Method for checking the compliance of a workpiece, comprising the following steps: estimating a risk of non-compliance of characteristic on the basis of a law of probability associated with the characteristic; and verifying whether the estimated risk of non-compliance satisfies a decision criterion and, if so, declaring that the workpiece is compliant for characteristic; if not, measuring a value of the characteristic, determining whether or not the workpiece is compliant based on the measured value, and updating the law of probability associated with characteristic based on the measured value.

IPC Classes  ?

  • G05B 19/418 - Total factory control, i.e. centrally controlling a plurality of machines, e.g. direct or distributed numerical control (DNC), flexible manufacturing systems (FMS), integrated manufacturing systems (IMS), computer integrated manufacturing (CIM)

23.

CIRCUIT FOR CONTROLLING POWER TRANSISTORS OF AN INVERTER ARM

      
Application Number 18260058
Status Pending
Filing Date 2022-01-21
First Publication Date 2024-03-07
Owner SAFRAN (France)
Inventor
  • Le, Thanh Long
  • Ngoua Teu Magambo, Jean Sylvio

Abstract

A control circuit for a first switch includes at least one transistor, the first switch being arranged in series with a second switch in an inverter arm of an electrical power supply device supplying a load connected to the mid-point of the series arrangement of the first and second switch. The control circuit is configured to adjust the gate-source voltage of the at least one transistor of the first switch according to a control scheme including, during a deactivation period of the first switch, the increase of the gate-source voltage in a time window including the deactivation of the second switch and the reduction of the gate-source voltage in a time window including the activation of the second switch.

IPC Classes  ?

  • H02M 7/539 - Conversion of dc power input into ac 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, e.g. single switched pulse inverters with automatic control of output wave form or frequency
  • B64D 41/00 - Power installations for auxiliary purposes
  • H02M 1/088 - Circuits specially adapted for the generation of control voltages for semiconductor devices incorporated in static converters for the simultaneous control of series or parallel connected semiconductor devices
  • H03K 17/0812 - Modifications for protecting switching circuit against overcurrent or overvoltage without feedback from the output circuit to the control circuit by measures taken in the control circuit

24.

HYBRID TURBOFAN ENGINE FOR AN AIRCRAFT, COMPRISING A MOTOR/GENERATOR COOLED BY HEAT PIPES

      
Application Number 18261443
Status Pending
Filing Date 2022-01-07
First Publication Date 2024-02-29
Owner
  • SAFRAN (France)
  • SAFRAN AIRCRAFT ENGINES (France)
Inventor
  • Sibilli, Thierry
  • Millier, Vincent François Georges
  • Guillotel, Loïc Paul Yves

Abstract

A hybrid turbofan engine for an aircraft, comprising a fan, an electric motor/generator and a gas generator, the engine comprising, between the fan and a splitter that separates the flows, an internal wall for delimiting an air duct, situated upstream of inlet guide vanes of a primary duct, and, upstream of outlet guide vanes, an internal upstream wall for delimiting a secondary duct, the motor/generator having a stator carried by a stator support fixed to a stator part of the engine. According to the invention, a plurality of heat pipe for cooling the motor/generator are provided, each heat pipe having an evaporation section fixed to the stator support, and a condensation section fixed to the internal wall or the internal upstream wall.

IPC Classes  ?

  • F01D 15/10 - Adaptations for driving, or combinations with, electric generators
  • B64D 27/24 - Aircraft characterised by the type or position of power plant using steam, electricity, or spring force
  • F02C 7/12 - Cooling of plants
  • F02K 3/115 - Heating the by-pass flow by means of indirect heat exchange

25.

IMPROVED METHOD FOR MANUFACTURING A PART BY ADDITIVE MANUFACTURING

      
Application Number 18261763
Status Pending
Filing Date 2022-01-11
First Publication Date 2024-02-29
Owner SAFRAN (France)
Inventor
  • Voiron, Mickaël
  • Gricourt, Thomas
  • Ovaere, Nicolas
  • Vial, Matthieu

Abstract

Method for manufacturing an aeronautical part by additive manufacturing, the part to be manufactured extending around a central axis and comprising at least two walls angled with respect to one another and connected to one another by means of at least one connection section comprised in a connection plane perpendicular to the central axis, the method comprising: providing a digital model of the part to be manufactured, orienting the digital model with respect to a vertical construction direction of the part so that the central axis of the part has an angle β of between 0.1° and 1°; and manufacturing the part by additive manufacturing from the digital model obtained in the orientation step.

IPC Classes  ?

  • B22F 10/80 - Data acquisition or data processing
  • B22F 10/47 - Structures for supporting workpieces or articles during manufacture and removed afterwards characterised by structural features
  • B22F 10/66 - Treatment of workpieces or articles after build-up by mechanical means
  • B33Y 10/00 - Processes of additive manufacturing
  • B33Y 40/20 - Post-treatment, e.g. curing, coating or polishing
  • B33Y 50/00 - Data acquisition or data processing for additive manufacturing
  • F01D 25/16 - Arrangement of bearings; Supporting or mounting bearings in casings

26.

METHOD FOR PROCESSING VOLUME IMAGES BY PRINCIPAL COMPONENT ANALYSIS

      
Application Number 18259488
Status Pending
Filing Date 2021-12-24
First Publication Date 2024-02-15
Owner
  • SAFRAN (France)
  • SAFRAN AIRCRAFT ENGINES (France)
  • ECOLE NORMALE SUPERIEURE PARIS- SACLAY (France)
  • CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE (France)
Inventor
  • Schneider-Die-Gross, Julien Paul
  • Jailin, Clément
  • Mendoza Quispe, Arturo
  • Roux, Stéphane

Abstract

Method for processing a plurality of X-ray tomography volume images each associated with a part, the plurality of volume images comprising a reference volume image, including: a step of correlating volume images to obtain a displacement field between each image and the reference image, to obtain a plurality of displacement fields minimizing the difference between the volume images, a processing by a dimensionality reduction method of the plurality of the image displacement fields to express them according to eigenmodes, and a statistical analysis of the fields expressed according to the eigenmodes.

IPC Classes  ?

27.

Stator assembly

      
Application Number 18271539
Grant Number 12000310
Status In Force
Filing Date 2022-01-04
First Publication Date 2024-02-15
Grant Date 2024-06-04
Owner SAFRAN (France)
Inventor
  • Parmentier, Nicolas Claude
  • Riera, William Henri Joseph

Abstract

A stator assembly including plural stator vanes distributed around an axis of revolution of the stator assembly, a chord of the stator vane, taken at a root of the stator vane, not overlapping, in the direction of the axis of revolution, a chord of an adjacent stator vane, taken at a root of the adjacent stator vane, and a chord of the stator vane, taken at a tip of the stator vane, overlapping, in the direction of the axis of revolution, a chord of the adjacent stator vane, taken at a tip of the adjacent stator vane.

IPC Classes  ?

  • F01D 9/04 - Nozzles; Nozzle boxes; Stator blades; Guide conduits forming ring or sector
  • B64C 11/00 - Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft

28.

PLATE HEAT EXCHANGER COMPRISING PROFILED GUIDE ELEMENTS

      
Application Number 18257243
Status Pending
Filing Date 2021-12-15
First Publication Date 2024-02-08
Owner SAFRAN (France)
Inventor Toubiana, Ephraim

Abstract

A plate heat exchanger, in particular for an aircraft turbo machine, between a first fluid and a second fluid, the first fluid being intended to circulate in a first direction and the second fluid being intended to circulate in a second direction different from the first direction, the heat exchanger having stacked stages for circulation of the first fluid, and profiled elements at the inlet and outlet of the stages, the profiled elements having a sawtooth-shaped cross-section and defining channels converging at the inlet of the stages and diverging at the outlet of the stages.

IPC Classes  ?

  • F28F 9/02 - Header boxes; End plates
  • F02C 7/14 - Cooling of plants of fluids in the plant
  • F28D 9/00 - Heat-exchange apparatus having stationary plate-like or laminated conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall

29.

METHOD AND LINE FOR MANUFACTURING A PANEL WITH MULTIPLE ACOUSTIC ELEMENTS FOR AN ACOUSTIC ATTENUATION STRUCTURE

      
Application Number 18259189
Status Pending
Filing Date 2022-01-13
First Publication Date 2024-02-08
Owner SAFRAN (France)
Inventor
  • Lanfant, Nicolas Pierre
  • Alglave, Hugues Laurent
  • Dunleavy, Patrick

Abstract

A method for continuously manufacturing a complex acoustic multi-element panel for an acoustic attenuation structure, the method including supplying a thermoplastic resin film at the entry of a stamping system including at least one pair of complementary cylinders, a heating of the thermoplastic resin film upstream of the entry of the stamping system, and a passage of the thermoplastic resin film between the at least one pair of complementary cylinders, the pair of complementary cylinders including a male cylinder with teeth radially protruding from the cylinder and a female cylinder with cavities on its radial surface, the cavities of the female cylinder being of shapes complementary to the shapes of the teeth of the male cylinder and a separation of the stamped film at the exit of the stamping system using a separator disposed at the exit of the stamping system between the stamped film and the female cylinder.

IPC Classes  ?

  • B29C 51/22 - Thermoforming apparatus having movable moulds or mould parts rotatable about an axis
  • B29C 35/08 - Heating or curing, e.g. crosslinking or vulcanising by wave energy or particle radiation
  • B29C 33/72 - Cleaning
  • B29C 51/04 - Combined thermoforming and prestretching, e.g. biaxial stretching
  • B29C 51/26 - Component parts, details or accessories; Auxiliary operations
  • B29C 51/44 - Removing or ejecting moulded articles
  • B29C 51/42 - Heating or cooling
  • B32B 3/28 - Layered products essentially comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products essentially having particular features of form characterised by a layer with cavities or internal voids characterised by a layer comprising a deformed thin sheet, e.g. corrugated, crumpled
  • B32B 27/08 - Layered products essentially comprising synthetic resin as the main or only constituent of a layer next to another layer of a specific substance of synthetic resin of a different kind
  • G10K 11/168 - Plural layers of different materials, e.g. sandwiches

30.

FUEL CONDITIONING SYSTEM AND METHOD CONFIGURED TO POWER AN AIRCRAFT TURBINE ENGINE USING FUEL FROM A CRYOGENIC TANK

      
Application Number 18264559
Status Pending
Filing Date 2022-02-24
First Publication Date 2024-02-08
Owner SAFRAN (France)
Inventor
  • Lambert, Pierre-Alain Marie Cyrille
  • Maalouf, Samer

Abstract

Disclosed is a fuel conditioning system (SC) configured to supply an aircraft turbine engine using fuel (Q) from a cryogenic tank (RC), the conditioning system (SC) comprising at least one pumping turbomachine (1), a first heat exchanger (31) configured to heat the fuel (Q) in the fuel circuit (CQ) by circulating an air stream (A), and at least one heating turbomachine (2) configured to supply an air flow (A) to the first heat exchanger (31), the heating turbomachine (2) comprising an air intake compressor (21), a combustion chamber (24) and an air exhaust turbine (22) configured to drive the air intake compressor (21), the combustion chamber (24) being supplied with air taken from the air flow (A) and with the fuel (Q) from the fuel circuit (CQ).

IPC Classes  ?

  • B64D 37/34 - Conditioning fuel, e.g. heating
  • F02C 7/224 - Heating fuel before feeding to the burner

31.

METHOD FOR MONITORING WEAR OF AN ACTUATOR

      
Application Number 18256827
Status Pending
Filing Date 2021-12-13
First Publication Date 2024-01-25
Owner
  • SAFRAN (France)
  • SAFRAN ELECTRONICS & DEFENSE (France)
Inventor
  • Assoumane, Amadou
  • El Badaoui, Mohammed
  • Mansouri, Badr
  • Venon, Audrey

Abstract

A method includes for each of the portions of a guide of the actuator, obtaining an operating signal measured when a movable element of the actuator travels over the guide portion in question, upon each of a plurality of successive activations of the actuator; for each of the guide portions, seeking wear of the actuator from the operating signals obtained for this guide portion; and locating the wear on the guide or on the motor according to the guide portions from which the wear has been found.

IPC Classes  ?

  • F16H 57/01 - Monitoring wear or stress of gearing elements, e.g. for triggering maintenance
  • F16H 25/22 - Screw mechanisms with balls, rollers, or similar members between the co-operating parts; Elements essential to the use of such members

32.

Composite vane for an aircraft turbine engine

      
Application Number 18021128
Grant Number 12006840
Status In Force
Filing Date 2021-08-09
First Publication Date 2024-01-25
Grant Date 2024-06-11
Owner Safran (France)
Inventor
  • Minervino, Matteo
  • Faivre D'Arcier, Pierre Jean
  • Lamouche, Damien Bruno
  • Lhommeau, Tony Alain Roger Joël

Abstract

Blower vane for an aircraft turbine engine, the vane comprising a blade connected to a root, the vane being made of a woven fibre-based composite material embedded in a polymeric resin, the vane further comprising a medium for identifying the vane, which is a radio-identification medium, the blower vane being characterised in that it comprises at least a first portion the fibres of which are only electrically conductive fibres, and at least a second portion the fibres of which are formed by a mixture of electrically conductive fibres and non-electrically conductive fibres, and in that the identification medium is located in or on the second portion.

IPC Classes  ?

  • F01D 5/28 - Selecting particular materials; Measures against erosion or corrosion
  • B29C 45/14 - Injection moulding, i.e. forcing the required volume of moulding material through a nozzle into a closed mould; Apparatus therefor incorporating preformed parts or layers, e.g. injection moulding around inserts or for coating articles
  • B29D 99/00 - Subject matter not provided for in other groups of this subclass
  • F01D 5/02 - Blade-carrying members, e.g. rotors
  • B29K 63/00 - Use of epoxy resins as moulding material
  • B29K 105/08 - Condition, form or state of moulded material containing reinforcements, fillers or inserts of continuous length, e.g. cords, rovings, mats, fabrics, strands or yarns
  • B29K 223/00 - Use of polyalkenes as reinforcement
  • B29K 267/00 - Use of polyesters as reinforcement
  • B29K 277/00 - Use of polyamides, e.g. polyesteramides, as reinforcement
  • B29K 307/04 - Carbon
  • B29K 309/08 - Glass
  • B29L 31/08 - Blades for rotors, stators, fans, turbines or the like, e.g. screw propellers

33.

FAIL-SAFE GUIDE DEVICE

      
Application Number 18254363
Status Pending
Filing Date 2021-11-15
First Publication Date 2024-01-18
Owner
  • SAFRAN (France)
  • SAFRAN ELECTRONICS & DEFENSE (France)
Inventor
  • Lawniczak, Rémi-Louis
  • Laurensan, Frédéric
  • Cartry, Thierry
  • Betbeder-Laüque, Xavier

Abstract

A device comprising: a stand; a frame rotatably mounted relative to the stand; a control arm rotatably mounted on the frame; a roll spider rotatably mounted on the frame; a pitch spider rotatably mounted on the control arm; a roll motor that is stationary relative to the frame and that includes a roll pin rotatably mounted on the roll spider; and a pitch motor that is stationary relative to the frame and that includes a pitch pin rotatably mounted on the pitch spider. A rotary connection device.

IPC Classes  ?

  • G05G 9/047 - Manually-actuated control mechanisms provided with one single controlling member co-operating with two or more controlled members, e.g. selectively, simultaneously the controlling member being movable in different independent ways, movement in each individual way actuating one controlled member only in which movement in two or more ways can occur simultaneously the controlling member being movable by hand about orthogonal axes, e.g. joysticks
  • F16C 35/067 - Fixing them in a housing

34.

HIGH-PRESSURE TURBINE VANE INCLUDING A CAVITY UNDER A SQUEALER TIP

      
Application Number 18256372
Status Pending
Filing Date 2021-12-08
First Publication Date 2024-01-18
Owner SAFRAN (France)
Inventor
  • Ostino, Leandre
  • Cariou, Romain Pierre
  • Pagnoni, Filippo
  • Paquin, Sylvain
  • Rollinger, Adrien Bernard Vincent

Abstract

The invention relates to a method for manufacturing a vane (11) of a turbine engine comprising a pressure-face wall (14) and a suction-face wall (15) spaced apart from one another, this vane (11) comprising a tip (S) with: a bottom wall (18) extending from the pressure-face wall (14) to the suction-face wall (15), each of which comprises a free edge (19, 21) extending beyond this bottom wall (18) to delimit, together with this bottom wall (18), a squealer shape (B); a partition wall (22) extending from the pressure-face wall (14) to the suction-face wall (15) and spaced apart from the bottom wall (18) to delimit, together with this bottom wall (18), a cavity (C) under the squealer tip; the method including: a moulding step to form at least the pressure-face wall (14), the suction-face wall (15) and the partition wall (22); —a step of forming the bottom wall (18) using an additive manufacturing method by adding metal material.

IPC Classes  ?

  • F01D 5/20 - Specially-shaped blade tips to seal space between tips and stator
  • B23K 26/342 - Build-up welding
  • B33Y 80/00 - Products made by additive manufacturing

35.

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

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

Abstract

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

IPC Classes  ?

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

36.

POWER TRANSMISSION SYSTEM COMPRISING AN IMPROVED OIL RECOVERY CHANNEL

      
Application Number 18254142
Status Pending
Filing Date 2021-11-24
First Publication Date 2024-01-04
Owner
  • SAFRAN (France)
  • SAFRAN TRANSMISSION SYSTEMS (France)
Inventor
  • Marcos Izquierdo, Juan-Luis
  • Cailler, Melody Elisabeth Laurent
  • Gedin, Patrice Jocelyn Francis
  • Serey, Jean-Pierre

Abstract

A power transmission system for an aircraft turbine engine including a speed reducer including a ring gear that is able to rotate about an axis X, formed from half-rings having annular flanges clamped together by first fastener. The reducer includes an annular channel for recovering centrifuged oil, having a U-shaped cross section, extending around the flanges, this channel being formed by an axial assembly of at least two parts and forming a fairing for the flanges and the first fastener intended to limit aerodynamic disturbances.

IPC Classes  ?

  • F16H 57/04 - Features relating to lubrication or cooling
  • 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 7/06 - Arrangement of bearings; Lubricating

37.

CASTING RING FOR OBTAINING A PRODUCT MADE OF TITANIUM ALLOY OR A TITANIUM-ALUMINUM INTERMETALLIC ALLOY AND METHOD USING SAME

      
Application Number 18255805
Status Pending
Filing Date 2021-12-02
First Publication Date 2023-12-28
Owner SAFRAN (France)
Inventor Sallot, Pierre Jean

Abstract

A casting ring having a first section made of a heat-conductive material and a second section made of a MAX phase alloy material, and a method for obtaining a product made of titanium alloy or a titanium-aluminum intermetallic compound by plasma torch melting, the alloy having an oriented structure, the method including heating the molten alloy surface in the casting ring with a plasma torch; cooling a cold zone of the casting ring over a length L1, the cooling forming a semi-solid crown of alloy; heating a hot zone of the casting ring over a length L2, thereby forming a solidification front, the flatness of which relative to a plane perpendicular to a drawing direction is less than 10°; and drawing the solidified alloy at a speed of more than 10−4 m/s in the drawing direction.

IPC Classes  ?

  • B22D 11/041 - Continuous casting of metals, i.e. casting in indefinite lengths into open-ended moulds for vertical casting
  • B22D 11/00 - Continuous casting of metals, i.e. casting in indefinite lengths
  • B22D 11/059 - Mould materials or platings
  • B22D 7/06 - Ingot moulds or their manufacture

38.

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

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

Abstract

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

IPC Classes  ?

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

39.

COUNTERCURRENT HEAT EXCHANGER FOR A TURBOMACHINE, TURBOMACHINE, AND METHOD FOR MANUFACTURING THE EXCHANGER

      
Application Number 18248290
Status Pending
Filing Date 2021-10-07
First Publication Date 2023-12-21
Owner SAFRAN (France)
Inventor
  • Toubiana, Ephraïm
  • Desarnaud, Fabien
  • Laurensan, Frédéric

Abstract

A counter-current heat exchanger for a turbomachine comprising a first and a second circuit, the first and the second circuit being respectively configured to receive a first gas flow and a second gas flow, each circuit including a secondary inlet manifold, an exchanging part and a secondary outlet manifold; the exchanging parts of the first circuit and of the second circuit being delimited by exchange walls configured to direct the first and the second gas flow along a first direction; and wherein the secondary inlet manifold and the secondary outlet manifold of the first circuit extend along a second direction substantially perpendicular to the first direction, and open onto a same face of the exchanger.

IPC Classes  ?

  • F02C 7/141 - Cooling of plants of fluids in the plant of working fluid
  • F28D 1/047 - Heat-exchange apparatus having stationary conduit assemblies for one heat-exchange medium only, the media being in contact with different sides of the conduit wall, in which the other heat-exchange medium is a large body of fluid, e.g. domestic or mo with the heat-exchange conduits immersed in the body of fluid with tubular conduits the conduits being bent, e.g. in a serpentine or zig-zag
  • F28F 9/02 - Header boxes; End plates

40.

Method for manufacturing a turbine engine vane

      
Application Number 18250796
Grant Number 11980934
Status In Force
Filing Date 2021-10-25
First Publication Date 2023-12-21
Grant Date 2024-05-14
Owner
  • SAFRAN (France)
  • SAFRAN AERO BOOSTERS (Belgium)
Inventor
  • Lefaux, Yann Jean-Pierre
  • Sallot, Pierre Jean

Abstract

A method for manufacturing a turbine engine vane a root connected to a blade extending in a longitudinal direction includes the steps of providing a root; and providing mold with a first cavity and a second cavity that together define a recess in which the vane is formed. The recess includes a first space in which the blade is formed and a second space in which the root is formed. The method further includes the steps of providing aluminum strips; positioning a fibrous reinforcement; arranging the vane root in the second space; and injecting a foam comprising aluminum or injecting an aluminum alloy into the first space of the recess of the mold such that the foam impregnates the fibrous reinforcement.

IPC Classes  ?

  • B22D 19/14 - Casting in, on, or around, objects which form part of the product the objects being filamentary or particulate in form
  • B22D 19/02 - Casting in, on, or around, objects which form part of the product for making reinforced articles
  • B22D 19/04 - Casting in, on, or around, objects which form part of the product for joining parts
  • B33Y 80/00 - Products made by additive manufacturing
  • C22C 47/06 - Pretreatment of the fibres or filaments by forming the fibres or filaments into a preformed structure, e.g. using a temporary binder to form a mat-like element
  • C22C 47/08 - Making alloys containing metallic or non-metallic fibres or filaments by contacting the fibres or filaments with molten metal, e.g. by infiltrating the fibres or filaments placed in a mould
  • C22C 49/06 - Aluminium
  • D03D 1/00 - Woven fabrics designed to make specified articles
  • D03D 15/242 - Woven fabrics characterised by the material, structure or properties of the fibres, filaments, yarns, threads or other warp or weft elements used characterised by the material of the fibres or filaments constituting the yarns or threads inorganic, e.g. basalt
  • F01D 5/30 - Fixing blades to rotors; Blade roots

41.

METHOD FOR MANUFACTURING A BLADE FOR A TURBOMACHINE

      
Application Number 18034166
Status Pending
Filing Date 2021-10-25
First Publication Date 2023-12-21
Owner
  • SAFRAN (France)
  • SAFRAN AERO BOOSTERS (Belgium)
Inventor
  • Lefaux, Yann Jean-Pierre
  • Sallot, Pierre Jean

Abstract

A method for manufacturing a blade for a turbine engine, including a root connected to a vane extending in a longitudinal direction, includes providing an assembly having a first part intended to form a root of the blade and a projecting second part projecting in the longitudinal direction from the first part; providing a mold comprising a first impression and a second impression delimiting together a cavity, said cavity comprising a first space and a second space; arranging the first part in the first space of the cavity and the second part in the second space of the cavity; and forming a third part by injecting an aluminium-based alloy in the cavity.

IPC Classes  ?

  • F01D 5/18 - Hollow blades; Heating, heat-insulating, or cooling means on blades
  • B22D 17/00 - Pressure die casting or injection die casting, i.e. casting in which the metal is forced into a mould under high pressure
  • B22D 19/00 - Casting in, on, or around, objects which form part of the product
  • B22D 19/04 - Casting in, on, or around, objects which form part of the product for joining parts

42.

ELECTRICAL CONDUCTOR COOLED BY PHASE CHANGE MATERIAL AND METHOD FOR THE MANUFACTURE THEREOF

      
Application Number 18247051
Status Pending
Filing Date 2021-09-28
First Publication Date 2023-11-16
Owner SAFRAN (France)
Inventor
  • Sallot, Pierre Jean
  • Ayat, Sabrina Siham
  • Fedi, Baptiste Joël Christian

Abstract

A method for manufacturing a conductor of a winding of a coil, includes manufacturing a heat-sink preform including a phase-change material, depositing a conductive element by layer deposition of electrically conductive material on the heat-sink preform, including inserting the heat-sink preform into an electrolytic solution of the electrically conductive material, and; electrodeposition for depositing the electrically conductive material on the heat-sink preform.

IPC Classes  ?

  • H02K 3/22 - Windings characterised by the conductor shape, form or construction, e.g. with bar conductors consisting of hollow conductors
  • H02K 9/20 - Arrangements for cooling or ventilating for machines with closed casing and closed-circuit cooling using a liquid cooling medium, e.g. oil wherein the cooling medium vaporises within the machine casing

43.

METHOD FOR WINDING A FILAMENT FOR AN ADDITIVE MANUFACTURING DEVICE

      
Application Number 18028421
Status Pending
Filing Date 2021-09-24
First Publication Date 2023-11-16
Owner
  • ECOLE NATIONALE SUPERIEURE D'ARTS ET METIERS (ENSAM) (France)
  • SAFRAN (France)
  • CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE (France)
  • CONSERVATOIRE NATIONAL DES ARTS ET METIERS (France)
Inventor
  • Theze, Alexis
  • Guinault, Alain
  • Regnier, Gilles

Abstract

The present invention relates to an assembly for a turbomachine turbine extending along an axis (X), comprising: —an ejection cone (100) comprising a radially outer annular wall (102) defining a flow duct for a flow of hot gases and a sound box radially arranged inside the outer annular wall (102), the sound box comprising a radially inner annular wall (104), —a connecting member (106) intended to be axially inserted between the exhaust housing and the ejection cone (100), the connecting member (106) comprising an upstream annular flange (108) intended to be attached to the exhaust housing and a plurality of downstream securing tabs (110) connected to the inner annular wall (104), —an annular sealing shroud (112) comprising an upstream portion surrounding the securing tabs (110) of the connecting member (106) so as to cover the spaces circumferentially located between the securing tabs (110) and axially located between the upstream annular flange (108) of the connecting member (106) and the radially inner annular wall (104).

IPC Classes  ?

  • B65H 54/02 - Winding and traversing material on to reels, bobbins, tubes, or like package cores or formers
  • B22F 10/22 - Direct deposition of molten metal
  • B33Y 40/00 - Auxiliary operations or equipment, e.g. for material handling
  • B22F 12/50 - Means for feeding of material, e.g. heads

44.

METHOD FOR MANUFACTURING A COMPOSITE MATERIAL PART HAVING A CELLULAR STRUCTURE AND CORRESPONDING PART

      
Application Number 18245199
Status Pending
Filing Date 2021-09-09
First Publication Date 2023-11-16
Owner SAFRAN (France)
Inventor
  • Lanfant, Nicolas Pierre
  • Dunleavy, Patrick

Abstract

A method for manufacturing a composite material part having a cellular structure that includes at least one cell delimited by walls. The method includes supplying at least a first core, providing a web of a first fibrous reinforcement comprising a plurality of long discontinuous fibers randomly distributed in a plane, and producing at least one strip of the first fibrous reinforcement. The method further includes producing a second fibrous reinforcement in the shape of a sock, inserting the first core into the sock, draping the strip around the sock containing the first core, placing the sock containing the first core and the wrapped strip in a mold, and thermocompression.

IPC Classes  ?

  • B29C 70/70 - Completely encapsulating inserts
  • B29C 70/22 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements using fibres of substantial or continuous length oriented in at least two directions forming a two dimensional structure
  • B29C 70/46 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs
  • F02K 1/54 - Nozzles having means for reversing jet thrust

45.

INSTRUMENTATION COMB FOR AN AIRCRAFT ENGINE WITH SENSORS AND INTEGRATED ELECTRONIC SYSTEM

      
Application Number 18256595
Status Pending
Filing Date 2021-11-30
First Publication Date 2023-11-16
Owner SAFRAN (France)
Inventor
  • D′almeida, Oscar
  • Masmoudi, Raouia Ghodhbane
  • Janfaoui, Sabri
  • Thomas, Patrick

Abstract

Instrumentation comb for an aircraft engine including a central tube with a longitudinal axis on which a determined number of orifices spaced apart along this longitudinal axis are drilled and a base forming a proximal end of this tube and intended to be fixed on a crankcase portion of the aircraft engine, each orifice being associated with a sensor for measuring a physical parameter of the aircraft engine and the base integrates a slave processing unit connected to each of the measuring sensors by a communication link able to receive in real time digital measurement data corresponding to the physical parameters measured by the measuring sensors and intended to be communicated to a master processing unit by a single communication link.

IPC Classes  ?

  • G01M 15/14 - Testing gas-turbine engines or jet-propulsion engines

46.

DOUBLE-FLOW HEAT EXCHANGER

      
Application Number 18027277
Status Pending
Filing Date 2021-09-22
First Publication Date 2023-11-09
Owner Safran (France)
Inventor
  • Toubiana, Ephraïm
  • Maalouf, Samer

Abstract

The invention relates to a heat exchanger comprising a support wall and a first plurality of fins that each stand proud from an outer surface of the support wall and are designed to have a first air flow pass over them. According to the invention, the heat exchanger comprises, downstream of the first plurality of fins, a second plurality of fins that each stand proud from the outer surface of the support wall, the first and second pluralities of fins being separated by distribution means which are configured in such a way that the first air flow flows outside the second plurality of fins and a second air flow flowing outside the first plurality of fins passes through the second plurality of fins.

IPC Classes  ?

  • F28F 13/06 - Arrangements for modifying heat transfer, e.g. increasing, decreasing by affecting the pattern of flow of the heat-exchange media

47.

SUBLAYER FOR A NICKEL-BASED SUPERALLOY FOR ENHANCING THE LIFETIME OF THE PARTS AND IMPLEMENTATION METHOD THEREOF

      
Application Number 18040322
Status Pending
Filing Date 2021-08-06
First Publication Date 2023-10-26
Owner SAFRAN (France)
Inventor Saboundji, Amar

Abstract

A nickel-based superalloy part includes a nickel-based superalloy substrate, and a metal sublayer covering the substrate, wherein the metal sublayer includes a first and a second layer, the first layer being located between the substrate and the second layer, the first layer including a first γ′-Ni3Al phase and a second γ-Ni phase, the second layer including a first γ′-Ni3Al phase, a second γ-Ni phase and a third β-NiAl phase, the average atomic fraction of aluminum in the second layer being strictly greater than the average atomic fraction of aluminum in the first layer.

IPC Classes  ?

  • C22C 19/05 - Alloys based on nickel or cobalt based on nickel with chromium
  • B32B 15/01 - Layered products essentially comprising metal all layers being exclusively metallic
  • F01D 5/28 - Selecting particular materials; Measures against erosion or corrosion

48.

SYSTEM AND METHOD FOR DETERMINING THE THREE-DIMENSIONAL PROFILE OF A SURFACE USING A PLENOPTIC CAMERA AND STRUCTURED LIGHTING

      
Application Number 17757795
Status Pending
Filing Date 2020-12-14
First Publication Date 2023-10-26
Owner SAFRAN (France)
Inventor
  • Michaud, Franck
  • Benaichouche, Ahmed Nasreddinne

Abstract

In the field of determining the three-dimensional profile of a surface, a system and a method for determining such a three-dimensional profile use a plenoptic camera and a structured lighting system. The method includes: acquiring a sequence of plenoptic images, each formed by a set of pixels each associated with a light intensity of an imaged surface element, and including a plurality of sub-images of the surface from different viewing angles, projecting onto the surface a sequence of structured images synchronised with the sequence of plenoptic images illumating each imaged surface element by a succession of light intensities different from the successions of light intensities which illuminate the other imaged surface elements, constructing, for each pixel of the plenoptic image, an intensity vector representing the succession of light intensities, and pairing each pixel of a sub-image with a pixel of another sub-image depending on a similarity of the intensity vectors.

IPC Classes  ?

  • G06T 7/557 - Depth or shape recovery from multiple images from light fields, e.g. from plenoptic cameras
  • G06V 10/141 - Control of illumination
  • H04N 23/957 - Light-field or plenoptic cameras or camera modules
  • G06T 7/521 - Depth or shape recovery from the projection of structured light
  • G06V 10/60 - Extraction of image or video features relating to illumination properties, e.g. using a reflectance or lighting model

49.

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

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

Abstract

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

IPC Classes  ?

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

50.

PROTECTION AGAINST OXIDATION OR CORROSION OF A HOLLOW PART MADE OF A SUPERALLOY

      
Application Number 18040767
Status Pending
Filing Date 2021-08-05
First Publication Date 2023-09-28
Owner SAFRAN (France)
Inventor
  • Rame, Jérémy
  • Saboundji, Amar
  • Bechelany, Mirna

Abstract

A protection method protects at least one hollow internal area of a turbine engine part made of a superalloy from oxidation and/or corrosion, wherein the at least one hollow inner area has been formed by means of at least one core made of a ceramic material limited by an external surface that surrounds it. Before bringing the superalloy around the core made of a ceramic material, the external surface is coated with a material that includes a nanometric layer of hafnium (Hf), and/or a micrometric layer of platinum (Pt), or A protection method protects at least one hollow internal area of a turbine engine part made of a superalloy from oxidation and/or corrosion, wherein the at least one hollow inner area has been formed by means of at least one core made of a ceramic material limited by an external surface that surrounds it. Before bringing the superalloy around the core made of a ceramic material, the external surface is coated with a material that includes a nanometric layer of hafnium (Hf), and/or a micrometric layer of platinum (Pt), or a mixture at least of hafnium and platinum.

IPC Classes  ?

  • F01D 5/28 - Selecting particular materials; Measures against erosion or corrosion
  • C23F 11/18 - Inhibiting corrosion of metallic material by applying inhibitors to the surface in danger of corrosion or adding them to the corrosive agent in other liquids using inorganic inhibitors

51.

LASER HEATING FOR THE MANUFACTURE OR REPAIR OF A TURBINE BLADE

      
Application Number 18002143
Status Pending
Filing Date 2021-06-09
First Publication Date 2023-09-28
Owner SAFRAN (France)
Inventor
  • Courapied, Damien Jonathan Julien
  • Marion, Guillaume Valentin Giamondo

Abstract

A device for laser heating of a mechanical part of the turbine blade or turbine blade element type, including: one or more laser emitters, for respectively emitting at least a first laser radiation at a first predetermined power towards a first target area of the part and for emitting a second laser radiation at a second predetermined power towards a second target area of the part, different from the first target area, the second predetermined power being different from the first predetermined power.

IPC Classes  ?

  • B23P 6/00 - Restoring or reconditioning objects
  • B23K 26/50 - Working by transmitting the laser beam through or within the workpiece

52.

DEVICE AND METHOD FOR DEPOSITING THICK METAL NITRIDE COATINGS BY THE SUPERCRITICAL FLUID ROUTE

      
Application Number 18006840
Status Pending
Filing Date 2021-07-21
First Publication Date 2023-09-28
Owner
  • SAFRAN (France)
  • CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE (France)
  • UNIVERSITE DE BORDEAUX (France)
Inventor
  • Cavarroc, Marjorie Christine
  • Aymonier, Cyril
  • Giroire, Baptiste Simon
  • Guillaume, Bertrand
  • Poulon, Angélique Nadine Jeanne
  • Aubert, Guillaume

Abstract

A device for depositing a thick metal nitride on a sample by supercritical fluids includes a first enclosure forming a first closed volume; a second enclosure placed in the first enclosure and delimited by internal walls transparent to electromagnetic radiation forming a second closed volume intended to include fluid under supercritical conditions; a heat transfer dielectric fluid circulating in the first volume around the second enclosure; a sample holder present in the second volume; an induction heating device surrounding the second enclosure; inlets for introducing a fluid and at least one precursor material into the second enclosure, and an outlet to purge the second volume.

IPC Classes  ?

  • C23C 18/12 - Chemical coating by decomposition of either liquid compounds or solutions of the coating forming compounds, without leaving reaction products of surface material in the coating; Contact plating by thermal decomposition characterised by the deposition of inorganic material other than metallic material

53.

AUTOTRANSFORMER, AUTOTRANSFORMER-RECTIFIER UNIT AND METHOD FOR CONNECTING A PIECE OF ELECTRICAL EQUIPMENT TO A THREE-PHASE GRID BY MEANS OF AN AUTOTRANSFORMER-RECTIFIER UNIT

      
Application Number 17998282
Status Pending
Filing Date 2021-05-12
First Publication Date 2023-08-31
Owner SAFRAN (France)
Inventor Biaujaud, Rémy

Abstract

A three-phase autotransformer including three output groups and three inputs each connected to each of the outputs of a respective output group by windings, the windings being configured so that, when each input has a respective input voltage applied thereto, the three input voltages having the same input amplitude, being 120° out of phase with each other and defining a neutral point: for each output group, a main output voltage, taken between a main output of said output group and the neutral point, has an amplitude greater than the input amplitude; and output voltages of the autotransformer belong to a same Reuleaux polygon, each output voltage being associated with a respective output and being equal to a voltage between said output and the neutral point.

IPC Classes  ?

  • H01F 30/02 - Auto-transformers
  • H02M 5/14 - Conversion of ac power input into ac power output, e.g. for change of voltage, for change of frequency, for change of number of phases without intermediate conversion into dc by static converters using transformers for conversion between circuits of different phase number
  • H01F 30/12 - Two-phase, three-phase or polyphase transformers

54.

METHOD FOR AUTOMATIC QUALITY INSPECTION OF AN AERONAUTICAL PART

      
Application Number 18006985
Status Pending
Filing Date 2021-06-29
First Publication Date 2023-08-31
Owner SAFRAN (France)
Inventor
  • Picard, Sylvaine
  • Belkhir, Nacim
  • Sartor, Enrico

Abstract

A method for automatic quality inspection of an aeronautical part, includes detecting faults on an image of the aeronautical part using a trained artificial neural network; training an auto-encoder on a database, by projecting each image of the database onto a small mathematical space in which the images follow a predefined probability law; for each image of the database, calculating a plurality of metrics; supervised training of a classifier from the calculated metrics; detecting faults or anomalies in the image of the aeronautical part using the auto-encoder and the classifier.

IPC Classes  ?

  • G06T 7/00 - Image analysis
  • G01N 35/00 - Automatic analysis not limited to methods or materials provided for in any single one of groups ; Handling materials therefor

55.

SUPPLY CIRCUIT FOR POWER MODULE WITH BUILT-IN ISOLATION TRANSFORMER AND ASSOCIATED POWER MODULE

      
Application Number 18003840
Status Pending
Filing Date 2021-06-28
First Publication Date 2023-08-24
Owner SAFRAN (France)
Inventor
  • Ngoua Teu Magambo, Jean Sylvio
  • Le, Thanh Long
  • Khazaka, Rabih

Abstract

Electrical power supply circuit for a power module comprising an electrical transformer, a first substrate having a first side including a heat sink and a second side, a second substrate having a first side including a heat sink and a second side, first metal tracks disposed on the second side of the first substrate, second metal tracks disposed on the second side of the second substrate, electrical connectors disposed between the first and second substrates to electrically connect a first metal track to a second metal track, the primary circuit of the electrical transformer comprising a first part of the first metal tracks and a first part of the second metal tracks, and the secondary circuit of the electrical transformer comprising a second part of the first metal tracks and a second part of the second metal tracks.

IPC Classes  ?

56.

METHOD FOR EVALUATING THE RELATIVE STATE OF AN AIRCRAFT ENGINE

      
Application Number 18004258
Status Pending
Filing Date 2021-06-21
First Publication Date 2023-08-24
Owner SAFRAN (France)
Inventor
  • Pineau, Edouard Guy Henri Marie
  • Razakarivony, Sébastien Philippe
  • Bonald, Thomas Pierre Louis

Abstract

A method for evaluating the state of an aircraft engine for a given flight, each flight of the aircraft being associated with one time-domain series, includes, each time maintenance of the aircraft is performed, creating a dataset including the time-domain series associated with each flight carried out between the maintenance and the preceding maintenance; creating a set of datasets including each created dataset and dividing it into a training set and a validating set; conjointly training an embedding function and a classifier, selecting a reference time-domain series from a time-domain series of the validating set; and computing a distance between the embedment associated with the time-domain series of the given flight and the embedment of the reference time-domain series, with a view to computing an indicator of engine state.

IPC Classes  ?

  • B64F 5/60 - Testing or inspecting aircraft components or systems
  • G06N 20/00 - Machine learning

57.

METHOD AND DEVICE FOR PHYSICALLY MEASURING ENVIRONMENTAL AND OPERATIONAL CONDITIONS

      
Application Number 18003168
Status Pending
Filing Date 2021-06-15
First Publication Date 2023-08-17
Owner SAFRAN (France)
Inventor
  • Hadjria, Rafik
  • D'Almeida, Oscar
  • Phan Huy, Minh Chau
  • Salhi, Nassim

Abstract

A method for measuring temperature and deformation of a part or structure on the basis of a single line of optical fiber having a single Bragg rating is provided. The method includes: interrogating the optical fiber based on two sampling frequencies; one being a low frequency and the other being a high frequency, said low frequency being suitable for sensing a slow rate of change corresponding to the temperature variation, and said high frequency being suitable for sensing a fast rate of change corresponding to vibrations; implementing an algorithmic block based on a blind-source-separation (BSS) technique, comprising a frequency analysis, a multivariate analysis and higher-order statistics; and returning to the time domain via an inverse Fourier transform.

IPC Classes  ?

  • G01L 1/24 - Measuring force or stress, in general by measuring variations of optical properties of material when it is stressed, e.g. by photoelastic stress analysis
  • G01K 11/3206 - Measuring temperature based on physical or chemical changes not covered by group , , , or using changes in transmittance, scattering or luminescence in optical fibres at discrete locations in the fibre, e.g. using Bragg scattering

58.

ACOUSTIC PANEL AND ASSOCIATED MANUFACTURING METHOD

      
Application Number 18012108
Status Pending
Filing Date 2021-06-07
First Publication Date 2023-08-10
Owner SAFRAN (France)
Inventor
  • Therriault, Daniel
  • Iervolino, Filippo
  • Pierre, Juliette
  • Piccirelli, Nicola
  • Ross, Annie
  • Costa Baptista, Josué

Abstract

An acoustic panel has two substantially parallel skins between which cavities forming Helmholtz resonators are arranged. One of the skins is bored with orifices, each of which opens into one of said cavities and forms a neck of the resonators. One or more of said cavities includes of a hollow structure having the shape of a triangular-based prism.

IPC Classes  ?

  • G10K 11/172 - Methods or devices for protecting against, or for damping, noise or other acoustic waves in general using resonance effects
  • G10K 11/168 - Plural layers of different materials, e.g. sandwiches
  • B32B 3/26 - Layered products essentially comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products essentially having particular features of form characterised by a layer with cavities or internal voids
  • B32B 3/12 - Layered products essentially comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products essentially having particular features of form characterised by a discontinuous layer, i.e. apertured or formed of separate pieces of material characterised by a layer of regularly-arranged cells whether integral or formed individually or by conjunction of separate strips, e.g. honeycomb structure
  • B33Y 80/00 - Products made by additive manufacturing
  • B32B 27/08 - Layered products essentially comprising synthetic resin as the main or only constituent of a layer next to another layer of a specific substance of synthetic resin of a different kind

59.

INSTALLATION FOR HEATING A CRYOGENIC FUEL

      
Application Number 17927556
Status Pending
Filing Date 2021-05-26
First Publication Date 2023-08-03
Owner SAFRAN (France)
Inventor
  • Jouan, Hugo Pierre Mohamed
  • Maalouf, Samer

Abstract

A system for heating cryogenic fuel includes a storage take, a supply line, a closed circuit, a cryogenic fuel heat exchanger, one or more working fluid heat exchangers, and a controller The storage tank stores the cryogenic fuel in a liquid state. The supply line connects the storage tank to a combustion chamber of an aircraft turbine engine. The closed circuit circulates a heat-transfer fluid. The cryogenic fuel heat exchanger heats the cryogenic fuel by the heat-transfer fluid. The closed circuit includes a pump for circulating the heat-transfer fluid and a closed expansion vessel connected to the closed circuit. The controller controls the pump to ensure a heat-transfer fluid flow rate inside the closed circuit so that the closed expansion vessel keeps the heat-transfer fluid circulating in the closed circuit at a pressure such that the heat-transfer fluid remains in the liquid state and does not change phase.

IPC Classes  ?

  • F02C 7/224 - Heating fuel before feeding to the burner
  • F02C 3/22 - Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products the fuel or oxidant being gaseous at standard temperature and pressure
  • F02C 7/141 - Cooling of plants of fluids in the plant of working fluid

60.

PROPULSION CHANNEL FOR AIRCRAFT

      
Application Number 17996306
Status Pending
Filing Date 2021-04-08
First Publication Date 2023-08-03
Owner SAFRAN (France)
Inventor
  • Viguier, Christophe Ludovic Jean-Claude
  • Petibon, Stéphane
  • Rougier, Florent

Abstract

A propulsion channel for aircraft at least one first dual-fed polyphase asynchronous rotating electric machine configured to be mechanically coupled to a turbine engine. The propulsion channel further includes at least one second polyphase rotating electric machine electrically coupled to the first asynchronous rotating electric machine, and a control and storage module configured to control the first polyphase asynchronous rotating electric machine. The module is connected to the first dual-feed polyphase asynchronous rotating electric machine as well as to the at least second polyphase rotating electric machine. The at least second polyphase rotating electric machine includes a polyphase synchronous rotating electric machine with permanent magnet.

IPC Classes  ?

  • H02P 7/343 - Arrangements for regulating or controlling the speed or torque of electric DC motors for regulating or controlling an individual dc dynamo-electric motor by varying field or armature current by master control with auxiliary power using Ward-Leonard arrangements in which both generator and motor fields are controlled
  • B64D 27/24 - Aircraft characterised by the type or position of power plant using steam, electricity, or spring force
  • B60L 50/15 - Electric propulsion with power supplied within the vehicle using propulsion power supplied by engine-driven generators, e.g. generators driven by combustion engines with additional electric power supply
  • B60L 53/24 - Using the vehicle's propulsion converter for charging

61.

Circuit for supplying fuel to an aeronautical cryogenic turbomachine and associated method

      
Application Number 18007082
Grant Number 11808204
Status In Force
Filing Date 2021-07-21
First Publication Date 2023-08-03
Grant Date 2023-11-07
Owner
  • SAFRAN (France)
  • ARIANEGROUP SAS (France)
Inventor
  • Lambert, Pierre-Alain
  • Jouan, Hugo Pierre Mohamed
  • Maalouf, Samer
  • Mabille De La Paumeliere, Louis-Vianney
  • Cruz, Carlos Alberto
  • Duri, Davide

Abstract

A fuel supply circuit for an aeronautical cryogenic turbomachine including: at least one cryogenic reservoir containing a liquid fuel topped with a boil-off gas and including a high-pressure liquid pump to supply at least one main propulsion device of the turbomachine with liquid fuel, an auxiliary turbomachine including an electric generator, a gas compressor to supply the auxiliary turbomachine with gaseous fuel, and a buffer gas reservoir connecting the gas compressor to the cryogenic reservoir to reinject gas into the cryogenic reservoir in order to maintain the pressure in the cryogenic reservoir above a predefined value, the electric generator supplying the high-pressure liquid pump and the gas compressor.

IPC Classes  ?

  • F02C 7/224 - Heating fuel before feeding to the burner
  • F02C 3/20 - Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products
  • F02C 7/14 - Cooling of plants of fluids in the plant
  • F02C 6/20 - Adaptations of gas-turbine plants for driving vehicles
  • F02C 9/40 - Control of fuel supply specially adapted to the use of a special fuel or a plurality of fuels
  • F02C 9/36 - Control of fuel supply characterised by returning of fuel to sump

62.

Method of characterizing a woven fibrous structure

      
Application Number 18006177
Grant Number 11783473
Status In Force
Filing Date 2021-08-03
First Publication Date 2023-07-20
Grant Date 2023-10-10
Owner
  • SAFRAN AIRCRAFT ENGINES (France)
  • SAFRAN (France)
  • CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQU (France)
  • ECOLE NORMALE SUPERIEURE PARIS-SACLAYE (France)
Inventor
  • Schneider-Die-Gross, Julien Paul
  • Belhaj Saad, Intisar
  • Mendoza Quispe, Arturo
  • Parra, Estelle Marie Laure
  • Roux, Stéphane

Abstract

The invention relates to a method for characterizing, from a volume image, a fibrous structure having a three-dimensional weaving between a plurality of warp yarns extending along a first direction and a plurality of weft yarns extending along a second direction perpendicular to the first one, the method comprising: a first processing of the volume image by filtering along a third direction perpendicular to the first and second directions so as to attenuate the periodic patterns along the third direction, obtaining a two-dimensional image corresponding to an intermediate plane along the third direction of the filtered volume image, a second processing of the two-dimensional image by filtering along the first or second direction so as to attenuate the periodic patterns, obtaining a one-dimensional profile representing the positions of warp or weft columns and corresponding to an intermediate line along the first or second direction.

IPC Classes  ?

  • G06T 5/40 - Image enhancement or restoration by the use of histogram techniques
  • G06T 7/00 - Image analysis
  • G06T 5/20 - Image enhancement or restoration by the use of local operators

63.

DETECTION AND LOCATION OF POWDER SPREADING ANOMALIES USING ACOUSTIC EMISSION MEASUREMENTS

      
Application Number 18002085
Status Pending
Filing Date 2021-06-09
First Publication Date 2023-07-13
Owner SAFRAN (France)
Inventor
  • Courapied, Damien Jonathan Julien
  • Cornu, Daniel André Jean
  • Giraud, Rémi Robert

Abstract

Device for manufacturing a part using a method of selective fusion or selective sintering on a powder bed comprising a build plate having a working surface, parallel to a first direction and to a second direction, on which surface the part is intended to be manufactured, a wiper which is placed on the working surface and capable of moving and spreading the powder in the first direction on the working surface, characterized in that it further includes at least two acoustic sensors which are fixed and spaced in the second direction on the wiper and capable of detecting an acoustic signal; a laser range finder pointing in the first direction and capable of determining a position of the wiper in the first direction; and a control system capable of detecting an anomaly on the basis of said acoustic signal and of determining a position of the anomaly.

IPC Classes  ?

  • B22F 10/28 - Powder bed fusion, e.g. selective laser melting [SLM] or electron beam melting [EBM]
  • B22F 10/37 - Process control of powder bed aspects, e.g. density
  • B22F 10/85 - Data acquisition or data processing for controlling or regulating additive manufacturing processes
  • B22F 12/67 - Blades
  • B22F 12/90 - Means for process control, e.g. cameras or sensors

64.

Installation for supplying cryogenic fuel to the combustion chamber of a turbine engine

      
Application Number 17999832
Grant Number 11846234
Status In Force
Filing Date 2021-05-27
First Publication Date 2023-07-06
Grant Date 2023-12-19
Owner SAFRAN (France)
Inventor
  • Sibilli, Thierry
  • Rebholz, Sarah

Abstract

An installation for supplying a cryogenic fuel to a combustion chamber of a turbine engine of an aircraft including a tank, a mixing chamber, and one or more heat exchangers. The tank stores cryogenic fuel in a and connects to a combustion chamber for supplying the combustion chamber with cryogenic fuel in the supercritical or gaseous state. The one or more heat exchangers are provided between the cryogenic fuel and air of an air-conditioning circuit of the aircraft, mounted in a line connecting the tank for cryogenic fuel to the mixing chamber and in a line to be connected to the air-conditioning circuit of the aircraft, the heat exchange taking place therein so as to cool the air of the air-conditioning circuit of the aircraft and to increase the temperature of the cryogenic fuel coming from the tank.

IPC Classes  ?

  • F02C 7/224 - Heating fuel before feeding to the burner
  • F02C 3/20 - Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products
  • F02C 7/14 - Cooling of plants of fluids in the plant

65.

Cryogenic fuel supply system for a turbine engine combustion chamber

      
Application Number 17927567
Grant Number 11920518
Status In Force
Filing Date 2021-05-25
First Publication Date 2023-07-06
Grant Date 2024-03-05
Owner SAFRAN (France)
Inventor Jouan, Hugo Pierre Mohamed

Abstract

A cryogenic fuel supply system includes a storage tank, a mixing chamber, an auxiliary heating device, a heat exchanger, and flow distribution devices, and a controller. The storage tank stores cryogenic fuel in a liquid state. The mixing chamber receives various flows of cryogenic fuel in a supercritical or gaseous state, the mixing chamber being connected to a combustion chamber to supply the combustion chamber with cryogenic fuel in the supercritical or gaseous state. The auxiliary heating device heats the cryogenic fuel. The heat exchanger assembly includes a cryogenic fuel/oil heat exchanger and a heat exchanger between the cryogenic fuel and the air circulating in a primary duct of the turbine engine. A flow distribution device is upstream of the auxiliary heating device, and one or more flow distribution devices are disposed upstream of the heat exchanger assembly. The controller controls opening and closing of the flow distribution devices.

IPC Classes  ?

  • F02C 7/224 - Heating fuel before feeding to the burner

66.

Vane made of composite material comprising metallic reinforcements, and method for manufacturing such a vane

      
Application Number 17996024
Grant Number 11795836
Status In Force
Filing Date 2021-04-12
First Publication Date 2023-06-15
Grant Date 2023-10-24
Owner SAFRAN (France)
Inventor
  • Iglesias Cano, Célia
  • Masson, Antoine Hubert Marie Jean
  • Obert, Enrico Giovanni

Abstract

A method for manufacturing a blade made of composite material for a turbine engine, in particular of an aircraft, the steps of injecting a resin in order to impregnate a fibrous preform woven in three dimensions and polymerizing the resin so as to form the blade that includes an airfoil, one longitudinal end of which is connected to a platform. The platform includes pressure and suction portions connected to the airfoil by a fillet, wherein a separation is formed in the fibrous preform between the pressure and suction portions. The method further includes reinforcing a leading edge of the airfoil; and reinforcing the fillets by integration of a metal reinforcement on at least one part of the pressure and suction portions of the platform and in the separation.

IPC Classes  ?

  • F01D 25/00 - Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
  • B29C 45/14 - Injection moulding, i.e. forcing the required volume of moulding material through a nozzle into a closed mould; Apparatus therefor incorporating preformed parts or layers, e.g. injection moulding around inserts or for coating articles
  • B29C 45/16 - Making multilayered or multicoloured articles
  • F01D 9/04 - Nozzles; Nozzle boxes; Stator blades; Guide conduits forming ring or sector
  • B29K 307/04 - Carbon
  • B29K 705/08 - Transition metals
  • B29L 31/08 - Blades for rotors, stators, fans, turbines or the like, e.g. screw propellers
  • B29C 64/147 - Processes of additive manufacturing using only solid materials using sheet material, e.g. laminated object manufacturing [LOM] or laminating sheet material precut to local cross sections of the 3D object
  • B29C 70/02 - Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising combinations of reinforcements and fillers incorporated in matrix material, forming one or more layers, with or without non-reinforced or non-filled layers
  • B29C 70/08 - Fibrous reinforcements only comprising combinations of different forms of fibrous reinforcements incorporated in matrix material, forming one or more layers, with or without non-reinforced layers
  • B29C 64/205 - Means for applying layers
  • B29C 70/20 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements using fibres of substantial or continuous length oriented in a single direction, e.g. roving or other parallel fibres
  • B29C 70/88 - Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts characterised primarily by possessing specific properties, e.g. electrically conductive or locally reinforced

67.

DEVICE FOR REGULATING THE PRESSURE OF AN AIRCRAFT CRYOGENIC FUEL TANK

      
Application Number 17927610
Status Pending
Filing Date 2021-05-25
First Publication Date 2023-06-01
Owner SAFRAN (France)
Inventor
  • Jouan, Hugo Pierre Mohamed
  • Lambert, Pierre-Alain
  • Piaton, Valery Pascal Marc Marie

Abstract

A pressure regulating device includes an on-board storage tank, a mixing chamber, first and second lines, a recirculation line, a pressure sensor and a controller. The storage tank stores and supplies cryogenic fuel to a combustion chamber and includes a booster pump. The first line supplies cryogenic fuel in the liquid state and includes a pressurizing pump and a first regulation valve. The second line supplies cryogenic fuel in the gaseous state and includes a compressor and a first control valve. The recirculation line includes a second regulation valve and with a first heat exchanger. The pressure sensor detects the pressure inside the storage tank. The controller receives the pressure and controls the first and second regulation valves, the first control valve, the pressurizing pump, the booster pump and the compressor, as a function of a value of a setpoint pressure inside the storage tank.

IPC Classes  ?

68.

DEVICE FOR MEASURING AN OPERATING VARIABLE OF A TYRE

      
Application Number 17913065
Status Pending
Filing Date 2021-03-22
First Publication Date 2023-06-01
Owner
  • SAFRAN (France)
  • SAFRAN ELECTRONICS & DEFENSE (France)
  • SAFRAN LANDING SYSTEMS (France)
  • COMPAGNIE GENERALE DES ETABLISSEMENTS MICHELIN (France)
Inventor
  • Destraves, Julien
  • Fagot-Revurat, Lionel
  • Bailly, Éric
  • Canu, Antoine
  • Vera, David

Abstract

The invention relates to a device for measuring an operating variable, to be fitted onto a tyre, comprising: an electronic circuit distributed over a first face of an electronic board and comprising a sensor; a protective housing at least partially covering the electronic circuit; and at least one first antenna wire having one end galvanically connected to the electronic circuit and integrally extending so as to project laterally from the housing; The invention relates to a device for measuring an operating variable, to be fitted onto a tyre, comprising: an electronic circuit distributed over a first face of an electronic board and comprising a sensor; a protective housing at least partially covering the electronic circuit; and at least one first antenna wire having one end galvanically connected to the electronic circuit and integrally extending so as to project laterally from the housing; According to the invention, the housing comprises a lateral portion which projects substantially tangentially to a proximal end portion of the first wire in accordance with the generatrix of said first wire.

IPC Classes  ?

  • B60C 23/04 - Signalling devices actuated by tyre pressure mounted on the wheel or tyre
  • B29D 30/00 - Producing pneumatic or solid tyres or parts thereof
  • G01L 17/00 - Devices or apparatus for measuring tyre pressure or the pressure in other inflated bodies
  • G01L 19/00 - MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE - Details of, or accessories for, apparatus for measuring steady or quasi-steady pressure of a fluent medium insofar as such details or accessories are not special to particular types of pressure gauges
  • G01L 19/06 - Means for preventing overload or deleterious influence of the measured medium on the measuring device or vice versa
  • G01L 19/08 - Means for indicating or recording, e.g. for remote indication
  • G01L 19/14 - Housings
  • G01L 9/00 - Measuring steady or quasi-steady pressure of a fluid or a fluent solid material by electric or magnetic pressure-sensitive elements; Transmitting or indicating the displacement of mechanical pressure-sensitive elements, used to measure the steady or quasi-steady pressure of a fluid or fluent solid material, by electric or magnetic means
  • H01Q 1/22 - Supports; Mounting means by structural association with other equipment or articles
  • H01Q 9/28 - Conical, cylindrical, cage, strip, gauze or like elements having an extended radiating surface; Elements comprising two conical surfaces having collinear axes and adjacent apices and fed by two-conductor transmission lines

69.

GENERATOR COMMON CORE WINDING

      
Application Number 17922898
Status Pending
Filing Date 2020-05-06
First Publication Date 2023-06-01
Owner
  • SAFRAN POWER USA, LLC (USA)
  • SAFRAN (France)
Inventor
  • Sorkin, Lev
  • Burger, Matthew Thomas
  • Roggia, Sara
  • Mischuk, Sergey

Abstract

A variable frequency generator (VFG) may include a housing, a shaft, a rotor, and a stator with slots. The VFG also includes a first set of stator windings including a first subset of windings and a second subset of windings and a second set of stator windings including a first subset of windings and a second subset of windings. The windings of the first subset of the first set of stator windings are co-located with the windings of the first subset of the second set of stator windings so as to share a common slot of the plurality of slots of the stator. Further, the windings of the second subset of the first set of stator windings are co-located with the windings of the second subset of the second set of stator windings so as to share a common alternative slot of the plurality of slots of the stator.

IPC Classes  ?

  • H02K 3/28 - Layout of windings or of connections between windings
  • H02K 1/16 - Stator cores with slots for windings
  • H02K 19/34 - Generators with two or more outputs

70.

NON-DESTRUCTIVE TESTING OF A MECHANICAL PART MADE OF A POLYCRYSTALLINE MATERIAL

      
Application Number 17995296
Status Pending
Filing Date 2021-03-31
First Publication Date 2023-05-25
Owner
  • SAFRAN (France)
  • CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE (France)
  • ECOLE SUPERIEURE DE PHYSIQUE ET DE CHIMIE INDUSTRIELLE DE LA VILLE DE PARIS (France)
Inventor
  • Brutt, Cecile
  • Gerardin, Benoit
  • Aubry, Alexandre
  • Derode, Arnaud
  • Prada, Claire

Abstract

A device, for non-destructive testing of a mechanical part made of a polycrystalline material, includes: an ultrasonic probe including a two-dimensional array of transducers capable of emitting and receiving signals at different excitation angles; and a processing module suitable for controlling the emission and the reception of the transducers, for processing the signals received by the transducers so as to express the signals received by the ultrasonic probe in two planar wave planes constructed from the emission and reception wave vectors of the probe, and for deducing therefrom information representative of the three-dimensional orientation of the fiber structure of the mechanical part.

IPC Classes  ?

71.

SYSTEM FOR DETERMINING THE ANGULAR SETTING OF AN ANNULAR ROW OF STATOR VANES

      
Application Number 17995520
Status Pending
Filing Date 2021-04-09
First Publication Date 2023-05-18
Owner SAFRAN (France)
Inventor
  • Giannakakis, Panagiotis
  • Riera, William Henri Joseph

Abstract

A method determines the angular setting (β_2) of an annular row of stator vanes arranged downstream of a pusher propeller of a propulsion system with a longitudinal axis. The annular row of stator vanes receives an air flow having a velocity (V2) including a longitudinal component (Viz) and a tangential component (V_iθ) associated with the velocity of gyration generated by the pusher propeller. The method includes the steps of establishing a theoretical model of the pusher propeller using a power (P1) and a mechanical speed (N1) associated with said pusher propeller, and flight conditions that include a velocity of the airflow incident on the pusher propeller, the altitude of said propulsion system and ambient temperature. The method further includes the step of determining an angular setting (β_1) of the pusher propeller from the theoretical model.

IPC Classes  ?

  • B64D 45/00 - Aircraft indicators or protectors not otherwise provided for
  • B64F 5/60 - Testing or inspecting aircraft components or systems

72.

DEVICE FOR MEASURING TYRE PRESSURE

      
Application Number 17906935
Status Pending
Filing Date 2021-03-22
First Publication Date 2023-05-18
Owner
  • SAFRAN (France)
  • SAFRAN ELECTRONICS & DEFENSE (France)
  • SAFRAN LANDING SYSTEMS (France)
  • COMPAGNIE GENERALE DES ETABLISSEMENTS MICHELIN (France)
Inventor
  • Canu, Antoine
  • Bailly, Eric
  • Vera, David
  • Neba, Eric-Carin
  • Arnoux, Michaël

Abstract

A pressure measuring device for a tyre includes an electronic circuit distributed over a first face and a second face of an electronic board and comprising a pressure sensor mounted on the first face of said electronic board; an antenna connected to the electronic circuit; a first housing part covering the first face such that together they delimit a first volume, and comprising channels fluidically connecting the first volume to the outside; a second housing part covering the second face such that together they delimit a second volume, and having a base for resting against an inner surface of a tread of the tyre, the second housing part being arranged such that the antenna projects laterally with respect to said second housing part and the housing has a centre of gravity located in the second volume spaced apart from the electronic board.

IPC Classes  ?

  • B60C 23/04 - Signalling devices actuated by tyre pressure mounted on the wheel or tyre
  • G01L 19/14 - Housings
  • H01Q 1/22 - Supports; Mounting means by structural association with other equipment or articles

73.

ROTATING ELECTRICAL MACHINE WITH SUPERCONDUCTING ELEMENTS AND CRYOGENIC ENCLOSURES

      
Application Number 17911085
Status Pending
Filing Date 2021-03-11
First Publication Date 2023-05-11
Owner
  • UNIVERSITE DE LORRAINE (France)
  • SAFRAN (France)
Inventor
  • Colle, Alexandre
  • Ayat, Sabrina Siham
  • Biaujaud, Rémy

Abstract

Disclosed is a rotating electrical machine with axial air gap, comprising two rotors, each provided with superconducting axial magnetic flux barrier elements around an axis of rotation and having, between them, axial magnetic flux passage areas, at least one armature, comprising windings and a superconducting field coil surrounding the elements and the armature and capable of inducing an axial magnetic field. Each armature is positioned between two of the rotors. The superconducting elements of the rotors are coaxial with one another and also the flux passage areas. A first annular cryogenic enclosure encloses the field coil and a second cryogenic enclosure encloses the two rotors and the armature or only one rotor, with a third cryogenic enclosure around the other rotor without the armature.

IPC Classes  ?

  • H02K 55/04 - Dynamo-electric machines having windings operating at cryogenic temperatures of the synchronous type with rotating field windings
  • B64D 27/24 - Aircraft characterised by the type or position of power plant using steam, electricity, or spring force

74.

Propulsion system for an aircraft

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

Abstract

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

IPC Classes  ?

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

75.

METHOD FOR CONTROLLING A RECTIFIER CONNECTED TO A PERMANENT-MAGNET SYNCHRONOUS ELECTRIC GENERATOR TO PROVIDE A DIRECT VOLTAGE, CORRESPONDING DEVICE AND COMPUTER PROGRAM

      
Application Number 17907612
Status Pending
Filing Date 2021-03-25
First Publication Date 2023-05-04
Owner
  • SAFRAN (France)
  • SAFRAN ELECTRICAL & POWER (France)
Inventor
  • Saber, Christelle
  • Rougier, Florent
  • Florescu, Adrian
  • Nadheria, Mallika

Abstract

This method comprises: determining a first setpoint (Iq_ref) for a first vector component (Iq) of the phase currents (Ia, Ib, Ic) along a first axis (q) of a rotating reference frame (R) connected to a rotor (112) of the electric generator (108), and a second setpoint (Id_ref) for a second vector component (Id) of the phase currents (Ia, Ib, Ic) along a second axis (d) of the rotating reference frame (R), this second vector component (Id) of the phase currents (Ia, Ib, Ic) being intended to bring about defluxing of the rotor (112); and controlling the rectifier (118) on the basis of the first and second setpoints (Iq_ref, Id_ref) for the vector components (Iq, Id) of the phase currents (Ia, Ib, Ic). The first setpoint (Iq_ref) for the first vector component (Iq) of the phase currents (Ia, Ib, Ic) is determined on the basis of an external feedback loop designed to feedback-control a voltage on a DC bus or to regulate a current from a battery connected to the DC bus.

IPC Classes  ?

  • H02P 11/04 - Arrangements for controlling dynamo-electric converters for controlling dynamo-electric converters having a dc output

76.

METHOD AND SYSTEM FOR NON-DESTRUCTIVE INSPECTION OF AN AERONAUTICAL COMPONENT

      
Application Number 17905241
Status Pending
Filing Date 2021-03-09
First Publication Date 2023-05-04
Owner SAFRAN (France)
Inventor Huck, Alexis Reynald Paul

Abstract

A method for the non-destructive inspection of an aeronautical component having a step of obtaining a plurality of digital images of a unit area of the aeronautical component, a step of estimating a characteristic image representative of the unit area, each pixel of the characteristic image having a characteristic vector, a step of dividing the characteristic image into a plurality of micro prediction zones, a step of comparing the characteristic vector of each pixel in each micro prediction zone with a previously estimated local statistical model of the micro prediction zone, the local model of a micro prediction zone being obtained by means of a learning algorithm from characteristic vectors of pixels in a micro learning zone of the annotated characteristic image which includes the micro prediction zone.

IPC Classes  ?

  • B64F 5/60 - Testing or inspecting aircraft components or systems
  • G06T 7/00 - Image analysis
  • G06T 3/40 - Scaling of a whole image or part thereof

77.

Turbomachine part or assembly of parts

      
Application Number 17794077
Grant Number 11982204
Status In Force
Filing Date 2021-01-19
First Publication Date 2023-05-04
Grant Date 2024-05-14
Owner SAFRAN (France)
Inventor
  • Riera, William Henri Joseph
  • Mondin, Gabriel Jacques Victor

Abstract

A turbomachine part or assembly of parts includes a first blade and a second blade, and platform from which the first blade and the second blade extend, The platform has, between a pressure side of the first blade and a suction side of the second blade a non-axisymmetric surface defining at least one fin, and a transverse section of the fin is asymmetric. The transverse section includes a first and a second oblique faces joining at a dorsal edge, the first oblique face is oriented toward the pressure side of the first blade, the second oblique face is oriented toward the suction side of the second blade, and the first oblique face has a steeper slope than the second oblique face.

IPC Classes  ?

78.

ACOUSTIC ATTENUATION STRUCTURE AND METHOD FOR MANUFACTURING SAME

      
Application Number 17915852
Status Pending
Filing Date 2021-03-30
First Publication Date 2023-04-27
Owner SAFRAN (France)
Inventor
  • Alglave, Hugues Laurent
  • Dunleavy, Patrick
  • Lanfant, Nicolas Pierre
  • Thomas, Cédric Pierre Michel

Abstract

A method for manufacturing an acoustic attenuation structure including a complex acoustic multi-element panel extending along a horizontal and a vertical direction and an acoustic skin covering one of horizontal faces of the complex acoustic multi-element panel, the complex acoustic multi-element panel including complex acoustic elements each having a shape gradually narrowing between a base and a tip and partitions surrounding each complex acoustic element to form a plurality of acoustic cells, the partitions extending along the vertical direction from the base of the complex acoustic elements, the complex acoustic multi-element panel being produced by injection of a filled or unfilled thermoplastic or thermosetting material. The complex acoustic multi-element panel and the plurality of partitions are produced as a single part by injection of a filled or unfilled thermoplastic or thermosetting material.

IPC Classes  ?

  • B29C 45/56 - Means for plasticising or homogenising the moulding material or forcing it into the mould using mould parts movable during or after injection, e.g. injection-compression moulding
  • G10K 11/162 - Selection of materials

79.

METHOD FOR MAKING A METAL PART WITH A COMPLEX GEOMETRY WITH A THIN WALL

      
Application Number 18082945
Status Pending
Filing Date 2022-12-16
First Publication Date 2023-04-20
Owner
  • SAFRAN (France)
  • Safran Nacelles (France)
Inventor
  • Soula, Aurelie
  • Sallot, Pierre

Abstract

A metal part with a wall thickness less than 5 mm includes a preform made from a flexible composite sheet, a flexible composite sheet segment, and an appended insert including a fastening portion that is sandwiched between a rear end of the preform and the flexible composite sheet segment. The flexible composite sheet segment encloses the fastening portion of the appended insert.

IPC Classes  ?

  • B22F 3/03 - Press-moulding apparatus therefor
  • B22F 3/10 - Sintering only
  • B22F 3/15 - Hot isostatic pressing
  • B22F 5/00 - Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product
  • B22F 1/102 - Metallic powder coated with organic material

80.

METHOD AND SYSTEM FOR SKELETONIZING STRANDS OF A COMPOSITE MATERIAL PART IN A 3D IMAGE

      
Application Number 17907351
Status Pending
Filing Date 2021-03-15
First Publication Date 2023-04-13
Owner SAFRAN (France)
Inventor
  • Brion, Véronique
  • Belkhir, Nacim
  • Hernandez Londono, Jorge Eduardo
  • Trullo Ramirez, Roger Fernando

Abstract

A method for skeletonizing the strands of a composite material part in a 3D image having a step of detecting oriented section centers of the strands and a link from each center to the closest center having the same orientation, the detection being carried out by means of at least one reference volume having an oriented centered strand pattern, the detection step having, for each reference volume: • a step of determining portions of the image, • a step of calculating a correlation score between the reference volume and each portion associated with the central voxel of each portion, so as to obtain a correlation score for each voxel of the image; and • a step of determining the strand centers corresponding to the voxels having a correlation score which corresponds to a local maximum.

IPC Classes  ?

  • G06T 7/181 - Segmentation; Edge detection involving edge linking
  • G06T 15/08 - Volume rendering
  • G06V 10/74 - Image or video pattern matching; Proximity measures in feature spaces

81.

X-RAY TOMOGRAPHIC RECONSTRUCTION METHOD AND ASSOCIATED DEVICE

      
Application Number 17913711
Status Pending
Filing Date 2021-03-22
First Publication Date 2023-04-13
Owner SAFRAN (France)
Inventor
  • Chapdelaine, Camille Jocelyn Roger
  • Picard, Sylvaine

Abstract

An x-ray tomographic method for reconstructing an object, includes, on the basis of a plurality of images, each image in the plurality of images corresponding to a projection of the object, reconstructing the object using an iterative reconstruction method so as to produce a plurality of reconstructions x(m) of the object.

IPC Classes  ?

  • G06T 11/00 - 2D [Two Dimensional] image generation

82.

METHOD FOR MANUFACTURING A PART OF NITRIDED STEEL

      
Application Number 17905017
Status Pending
Filing Date 2021-02-26
First Publication Date 2023-04-06
Owner SAFRAN (France)
Inventor
  • Badreddine, Jawad
  • Thibault, Simon

Abstract

A method for manufacturing a part of nitrided steel includes a step of nitriding the part. After nitriding, laser shocking is carried out on a surface of the nitrided part.

IPC Classes  ?

  • C21D 10/00 - Modifying the physical properties by methods other than heat treatment or deformation
  • C21D 8/00 - Modifying the physical properties by deformation combined with, or followed by, heat treatment
  • C21D 1/06 - Surface hardening
  • C23C 8/26 - Nitriding of ferrous surfaces
  • C21D 6/00 - Heat treatment of ferrous alloys

83.

METHOD FOR CONTROLLING A TURBOMACHINE COMPRISING AN ELECTRIC MACHINE

      
Application Number 17905970
Status Pending
Filing Date 2021-03-02
First Publication Date 2023-04-06
Owner SAFRAN (France)
Inventor
  • Jaljal, Nawal
  • Giannakakis, Panagiotis

Abstract

The invention relates to a method for controlling a turbomachine comprising a gas generator, the turbomachine comprising an electric machine forming a device for injecting torque into/removing torque from one of the low pressure/high pressure rotation shafts of said gas generator. Said method comprises a step of implementing a fuel control loop in order to determine a fuel flow setpoint into the combustion chamber, and comprising, in the event that at least one operability limit is reached, determining a corrected fuel flow setpoint, said corrected fuel flow setpoint exhibiting a difference in relation to the setpoint. Said method also comprises a step of implementing a torque control loop in order to determine a torque setpoint for the electric machine, and comprising determining a torque correction quantity as a function of said difference, said torque setpoint being determined as a function of said torque correction quantity.

IPC Classes  ?

  • F02C 9/56 - Control of fuel supply conjointly with another control of the plant with power transmission control
  • F02C 7/36 - Power transmission between the different shafts of the gas-turbine plant, or between the gas-turbine plant and the power user

84.

AIRCRAFT TURBINE ENGINE WITH A HYBRID COMPRESSOR

      
Application Number 17904670
Status Pending
Filing Date 2021-02-02
First Publication Date 2023-03-30
Owner SAFRAN (Republic of Korea)
Inventor
  • Parmentier, Nicolas Claude
  • Riera, William Henri Joseph

Abstract

The invention relates to an aircraft turbine engine (101) which comprises, downstream of the low pressure compressor of its low pressure body (104) and upstream of its combustion chamber (102), an electric motor (206) which is configured to rotate a rotor blade ring so as to generate a flow of air. Moreover, the rotational speed of the electric machine rotor is independent of the rotational speed of the compressor rotor.

IPC Classes  ?

  • F02K 5/00 - Plants including an engine, other than a gas turbine, driving a compressor or a ducted fan

85.

SYSTEM FOR LOCATING A WOVEN PREFORM TRACER

      
Application Number 17908020
Status Pending
Filing Date 2021-03-01
First Publication Date 2023-03-23
Owner SAFRAN (France)
Inventor
  • Lasjaunias, Benoît Vincent Pierre
  • Magro, Rémi
  • Venat, Romain

Abstract

A system for locating a strand including fibers of a first woven preform material, the preform including, at the surface, strands of fibers of a second material and the strand including fibers of the first material forming a tracer. The system further includes a camera; a light source emitting a non-polarized incident beam configured to be directed towards the preform; a polarizer configured to polarize the non-polarized incident beam before interacting with the preform in order to obtain a polarized incident beam; and a crossed analyzer; the first material being chosen from among glass, aramid and aluminum oxide; the second material being chosen from among carbon and silicon carbide; the camera being configured to film a reflected beam originating from the interaction of the polarized incident beam with the preform, the reflected beam having previously crossed the crossed analyzer, so as to locate the tracer of the preform.

IPC Classes  ?

  • G01N 21/21 - Polarisation-affecting properties
  • G02B 27/28 - Optical systems or apparatus not provided for by any of the groups , for polarising
  • B29C 45/14 - Injection moulding, i.e. forcing the required volume of moulding material through a nozzle into a closed mould; Apparatus therefor incorporating preformed parts or layers, e.g. injection moulding around inserts or for coating articles

86.

WOVEN FIBROUS PREFORM FOR PRODUCING A PART FROM COMPOSITE MATERIAL, IN PARTICULAR A TURBOMACHINE BLADE

      
Application Number 17795438
Status Pending
Filing Date 2021-01-19
First Publication Date 2023-03-23
Owner SAFRAN (France)
Inventor
  • Dambrine, Bruno Jacques Gérard
  • Marchal, Yann Didier Simon
  • Coupe, Dominique Marie Christian
  • Colot, Marc-Antoine

Abstract

A fibrous preform for forming the fibrous reinforcement of a composite material part, the fibrous preform being made as a single piece and obtained by three-dimensional weaving, the preform including first and second skins and a longitudinal stiffening portion connecting the first to the second skin, the longitudinal stiffening portion forming a stiffening element of the part in the longitudinal direction. The preform has an intermediate portion extending in the longitudinal direction between two end portions. The longitudinal stiffening portion includes, in the intermediate portion, longitudinal non-woven threads or strands held together by first transverse threads or strands coming from the first skin and second transverse threads or strands coming from the second skin. In the end portions, the longitudinal threads or strands of the longitudinal stiffening portion are woven with the transverse threads or strands.

IPC Classes  ?

  • D03D 25/00 - Woven fabrics not otherwise provided for
  • B29B 11/16 - Making preforms characterised by structure or composition comprising fillers or reinforcements
  • B29D 99/00 - Subject matter not provided for in other groups of this subclass
  • B29C 70/24 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements using fibres of substantial or continuous length oriented in at least three directions forming a three dimensional structure
  • F01D 5/28 - Selecting particular materials; Measures against erosion or corrosion

87.

NAVIGATION ASSISTANCE METHOD FOR A MOBILE CARRIER

      
Application Number 17796937
Status Pending
Filing Date 2021-02-03
First Publication Date 2023-03-16
Owner
  • SAFRAN (France)
  • ASSOCIATION POUR LA RECHERCHE ET LE DEVELOPPMENT DES METHODES ET PROCESSUS INDUSTRIELS (France)
Inventor
  • Chauchat, Paul
  • Barrau, Axel
  • Bonnabel, Silvère

Abstract

The present invention relates to a navigation assistance method for a mobile carrier (1) comprising an inertial navigation unit (10) comprising at least one inertial sensor (12), in which, over a determined observation window, the following steps are implemented by an estimation unit (11) of the inertial navigation unit (10): (E10) parametrisation of a non-linear system configured to estimate a navigation state of the mobile carrier (1) over a given time interval at an iteration n as a function of a kinematic model and/or measurements acquired by at least one inertial sensor (12); (E20) linearisation of the system so that the system expresses a navigation state at iteration n as a function of the state at iteration n−1 and a correction to this navigation state, said system being initialised by a first a priori state; (E21) estimating, by a Kalman filter and stochastic cloning, a first correction of a navigation state at iteration n; (E22) estimating a second correction of the navigation state at iteration n by an information filter operating in reverse and stochastic cloning; (E30) determining a third correction by merging the first and second corrections; and (E40) correcting the navigation state at iteration n as a function of the third correction, the corrected state being used at iteration n+1.

IPC Classes  ?

  • G01C 21/16 - Navigation; Navigational instruments not provided for in groups by using measurement of speed or acceleration executed aboard the object being navigated; Dead reckoning by integrating acceleration or speed, i.e. inertial navigation

88.

SUPERALLOY TURBOMACHINE PART WITH AN OPTIMIZED HAFNIUM CONTENT

      
Application Number 17797920
Status Pending
Filing Date 2021-02-02
First Publication Date 2023-03-09
Owner
  • SAFRAN AIRCRAFT ENGINES (France)
  • SAFRAN (France)
  • CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE (France)
  • UNIVERSITE DE LA ROCHELLE (France)
Inventor
  • Delautre, Joel
  • Audic, Christophe Philippe
  • Hamadi, Sarah
  • Jaquet, Virginie
  • Pedraza Diaz, Fernando
  • Pasquet, Annie

Abstract

A turbomachine part includes a nickel-based superalloy substrate including, in mass content, 5.0% to 8.0% cobalt, 6.5% to 10% chromium, 0.5% to 2.5% molybdenum, 5.0% to 9.0% tungsten, 6.0% to 9.0% tantalum, 4.5% to 5.8% aluminum, hafnium in a mass content between 500 ppm and 1100 ppm, and optionally including niobium in a mass content less than or equal to 1.5%, and optionally at least one of carbon, zirconium and boron each in a mass content less than or equal to 100 ppm, the remainder being composed of nickel and unavoidable impurities.

IPC Classes  ?

  • F01D 25/00 - Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
  • F02C 7/22 - Fuel supply systems
  • F01D 9/04 - Nozzles; Nozzle boxes; Stator blades; Guide conduits forming ring or sector
  • F23R 3/00 - Continuous combustion chambers using liquid or gaseous fuel
  • C22C 19/05 - Alloys based on nickel or cobalt based on nickel with chromium

89.

METHOD FOR COMMUNICATION ACCORDING TO A TDMA PROTOCOL BETWEEN A MASTER DEVICE AND AT LEAST ONE SLAVE DEVICE

      
Application Number 17759990
Status Pending
Filing Date 2021-03-15
First Publication Date 2023-03-02
Owner SAFRAN (France)
Inventor
  • Thomas, Patrick
  • Ghodhbane, Raouia

Abstract

Disclosed is a method for communication, according to a TDMA protocol, between a master device and at least one slave device, during which a plurality of frames are transmitted between the master device and the slave device, each frame being partitioned into a plurality of time intervals, at least one time interval having an analogue synchronization signal having an amplitude regulation portion in the form of a sine wave having a constant amplitude over a number of predetermined pulses, and an optimized synchronization portion in the form of a triangular amplitude modulation of the sine wave so as to determine a reference time.

IPC Classes  ?

  • H04J 3/06 - Synchronising arrangements
  • H04J 3/16 - Time-division multiplex systems in which the time allocation to individual channels within a transmission cycle is variable, e.g. to accommodate varying complexity of signals, to vary number of channels transmitted

90.

COATED TURBOMACHINE PART HAVING A NICKEL-BASED SUBSTRATE COMPRISING HAFNIUM

      
Application Number 17797947
Status Pending
Filing Date 2021-02-01
First Publication Date 2023-03-02
Owner
  • SAFRAN AIRCRAFT ENGINES (France)
  • SAFRAN (France)
  • CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE (France)
  • UNIVERSITE DE LA ROCHELLE (France)
Inventor
  • Delautre, Joel
  • Hamadi, Sarah
  • Pasquet, Annie
  • Jaquet, Virginie
  • Pedraza Diaz, Fernando
  • Audic, Christophe Philippe

Abstract

A turbomachine part includes (i) a nickel-based superalloy substrate including, in mass content, 5.0% to 8.0% cobalt, 6.5% to 10% chromium, 0.5% to 2.5% molybdenum, 5.0% to 9.0% tungsten, 6.0% to 9.0% tantalum, 4.5% to 5.8% aluminum, hafnium in a mass content greater than or equal to 2000 ppm, and optionally including niobium in a mass content less than or equal to 1.5%, and optionally at least one of carbon, zirconium and boron each in a mass content less than or equal to 100 ppm, the remainder being composed of nickel and unavoidable impurities; and (ii) a β-structured nickel aluminide coating covering the substrate.

IPC Classes  ?

  • F01D 5/28 - Selecting particular materials; Measures against erosion or corrosion
  • C22C 19/05 - Alloys based on nickel or cobalt based on nickel with chromium
  • C30B 29/52 - Alloys

91.

DEVICE FOR TRANSFERRING HEAT

      
Application Number 17911348
Status Pending
Filing Date 2021-02-19
First Publication Date 2023-02-23
Owner
  • SAFRAN (France)
  • SAFRAN ELECTRONICS & DEFENSE (France)
Inventor
  • Youssef, Toni
  • Azzopardi, Stéphane Joseph
  • Riou, Jean-Christophe

Abstract

The invention relates to a device (2) for transferring heat from a thermally conductive plate (3) capable of capturing the heat from a zone placed on a first side (32) of the plate, the device comprising at least one fin (35) placed on a second side (34) of the plate (30) opposite the first side (32) and having a duct (36) extending in a longitudinal direction (L) between a first end (38) connected to the plate and a second end (4) opposite the first end and which opens out, the duct (36) being connected to at least one Venturi-effect neck (42) bringing cooling air into the duct, the neck (42) being formed in the vicinity of the first end of the duct and the plate (30).

IPC Classes  ?

  • H01L 23/367 - Cooling facilitated by shape of device
  • H01L 23/467 - Arrangements for cooling, heating, ventilating or temperature compensation involving the transfer of heat by flowing fluids by flowing gases, e.g. air
  • H01L 23/373 - Cooling facilitated by selection of materials for the device
  • F28F 3/02 - Elements or assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with recesses, with corrugations
  • F28F 1/16 - Tubular elements or assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with projections, with recesses the means being only outside the tubular element and extending longitudinally the means being integral with the element, e.g. formed by extrusion
  • F28F 13/08 - Arrangements for modifying heat transfer, e.g. increasing, decreasing by affecting the pattern of flow of the heat-exchange media by varying the cross-section of the flow channels

92.

SYSTEM FOR MEASURING A PLURALITY OF PHYSICAL PARAMETERS AT A MEASUREMENT POINT WITH A MULTIMODE OPTICAL FIBER

      
Application Number 17759482
Status Pending
Filing Date 2021-01-22
First Publication Date 2023-02-16
Owner SAFRAN (France)
Inventor
  • Salhi, Nassim
  • Phan Huy, Minh Chau

Abstract

In the field of measuring physical parameters with a multimode optical fiber, a system for measuring P physical parameters at one or more measurement points has one or more multimode optical fibers. The system includes: a light source generating a source optical signal, a multimode measurement optical fiber transporting optical signals in at least M distinct second predetermined propagation modes, M being an integer greater than or equal to P, the measurement optical fiber including a measurement section reflecting the optical signals with a wavelength variable according to physical parameters to be measured, a detection device measuring wavelengths of the optical signals reflected by the measurement section, and an optical module generating M signals from the source optical signal, the M signals each being injected into the measurement optical fiber to propagate in one of the modes, the optical module also transferring the optical signals reflected toward the detection device.

IPC Classes  ?

  • G01D 5/353 - Mechanical means for transferring the output of a sensing member; Means for converting the output of a sensing member to another variable where the form or nature of the sensing member does not constrain the means for converting; Transducers not specially adapted for a specific variable using optical means, i.e. using infrared, visible or ultraviolet light with attenuation or whole or partial obturation of beams of light the beams of light being detected by photocells influencing the transmission properties of an optical fibre
  • G01K 11/3206 - Measuring temperature based on physical or chemical changes not covered by group , , , or using changes in transmittance, scattering or luminescence in optical fibres at discrete locations in the fibre, e.g. using Bragg scattering
  • G01L 1/24 - Measuring force or stress, in general by measuring variations of optical properties of material when it is stressed, e.g. by photoelastic stress analysis

93.

DEVICE AND METHOD FOR STOPPING AN ELECTRIC MACHINE FOR A TURBINE ENGINE

      
Application Number 17798340
Status Pending
Filing Date 2021-02-02
First Publication Date 2023-02-16
Owner SAFRAN (France)
Inventor Jaljal, Nawal

Abstract

An electrical assembly for an aeronautical turbomachine, including an electric machine configured to be disposed in a turbomachine and comprising a stator and a rotor comprising magnets, the assembly including a short-circuit detecting means, a hot air injecting means configured to draw hot air off the turbomachine at a temperature greater than the temperature of demagnetization of the magnets of the rotor, and to inject the drawn hot air onto the magnets of said rotor when the short-circuit detecting means detects the presence of a short-circuit in the electric machine, and a cool air injecting means, configured to draw cool air off the turbomachine and to inject it into an inner chamber of the turbomachine, the temperature of the cool air drawn by the cool air injecting means being less than the temperature of the hot air drawn by the hot air injecting means.

IPC Classes  ?

  • H02P 29/024 - Detecting a fault condition, e.g. short circuit, locked rotor, open circuit or loss of load
  • F02C 7/25 - Fire protection or prevention
  • H02K 9/19 - Arrangements for cooling or ventilating for machines with closed casing and closed-circuit cooling using a liquid cooling medium, e.g. oil
  • H02K 21/14 - Synchronous motors having permanent magnets; Synchronous generators having permanent magnets with stationary armatures and rotating magnets with magnets rotating within the armatures
  • F02C 6/08 - Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas the gas being bled from the gas-turbine compressor
  • F02C 7/32 - Arrangement, mounting, or driving, of auxiliaries

94.

COMPOSITE BLADE FOR AN AIRCRAFT ENGINE AND METHODS FOR MANUFACTURING AND REPAIRING SAME

      
Application Number 17779794
Status Pending
Filing Date 2020-11-23
First Publication Date 2023-02-02
Owner SAFRAN (France)
Inventor
  • Touze, Adrien
  • Lanfant, Nicolas Pierre
  • Picon, Romain
  • Sorgnard, Loïc

Abstract

A process for manufacturing a blade made of composite material for a turbomachine. The blade includes an airfoil having a pressure side and a suction side which extend from a leading edge to a trailing edge of the airfoil. The blade further includes a metal sheath that extends along the leading edge of the airfoil. The process includes the steps of: placing a preform, produced by three-dimensionally weaving fibers, in a mold, the sheath being positioned on an edge of the preform intended to form the leading edge of the airfoil; and injecting polymerizable resin into the mold to impregnate the preform so as to form the airfoil after solidifying. At least one double-sided adhesive film may be inserted between the sheath and the edge of the preform prior to injection of the resin.

IPC Classes  ?

  • F01D 5/28 - Selecting particular materials; Measures against erosion or corrosion
  • F01D 5/14 - Form or construction

95.

SUPERCONDUCTING BULK COMPRISING A CAVITY AND ASSOCIATED ELECTRIC MACHINE

      
Application Number 17784473
Status Pending
Filing Date 2020-12-07
First Publication Date 2023-02-02
Owner
  • SAFRAN (France)
  • UNIVERSITE DE LORRAINE (France)
Inventor
  • Ayat, Sabrina Siham
  • Colle, Alexandre
  • Biaujaud, Rémy

Abstract

The present invention relates to a superconducting pellet for a superconducting electrical machine, the superconducting pellet having a circumferential wall, the circumferential wall having: a first border, a second border opposite the first border, an inner face connecting the first border to the second border, an outer face opposite the inner face, and a cavity formed between the first border and the second border and defined by the inner face, and an additional wall which covers the first border or is flush with the first border so as to at least partially cover the cavity, or extends from the inner face at a distance from the first border and the second border so as to divide the cavity into two portions.

IPC Classes  ?

  • H02K 55/02 - Dynamo-electric machines having windings operating at cryogenic temperatures of the synchronous type
  • H02K 15/02 - Methods or apparatus specially adapted for manufacturing, assembling, maintaining or repairing of dynamo-electric machines of stator or rotor bodies
  • B64D 27/24 - Aircraft characterised by the type or position of power plant using steam, electricity, or spring force

96.

METHOD FOR MANUFACTURING A GRID MADE OF A COMPOSITE MATERIAL

      
Application Number 17757547
Status Pending
Filing Date 2020-12-17
First Publication Date 2023-01-26
Owner SAFRAN (France)
Inventor
  • Lanfant, Nicolas Pierre
  • Farrands, Maximilien Eddie
  • Geraud-Grosheny, Pierre Francois Robin

Abstract

The invention relates to a method for producing a grid made of composite material for straightening an air flow for an aircraft turbine engine. The described method is based on the use of longitudinal members (301) which have recesses (303) to allow the penetration of connecting elements (304) into said recesses during the manufacture of the grid.

IPC Classes  ?

  • B29C 70/42 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles
  • F02K 1/54 - Nozzles having means for reversing jet thrust
  • B29C 45/14 - Injection moulding, i.e. forcing the required volume of moulding material through a nozzle into a closed mould; Apparatus therefor incorporating preformed parts or layers, e.g. injection moulding around inserts or for coating articles
  • B29C 70/22 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements using fibres of substantial or continuous length oriented in at least two directions forming a two dimensional structure
  • B29C 70/14 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements using fibres of short length, e.g. in the form of a mat oriented

97.

METHOD FOR MONITORING A TURBOMACHINE, DEVICE, SYSTEM, AIRCRAFT AND COMPUTER PROGRAM PRODUCT

      
Application Number 17782451
Status Pending
Filing Date 2020-12-04
First Publication Date 2023-01-19
Owner
  • SAFRAN (France)
  • SAFRAN AIRCRAFT ENGINES (France)
Inventor
  • Abboud, Dany
  • El Badaoui, Mohammed
  • Tableau, Nicolas Paul

Abstract

Method for monitoring a turbomachine comprising a stator and a rotor, device, system, aircraft and computer program product. The method comprises a step of acquiring an input signal which represents a deformation of the stator or rotor of the turbomachine. The input signal has been acquired by a deformation gauge which is attached to the stator or rotor. The input signal comprises a first component which represents deformations of the stator or rotor which are caused by rotation of the rotor vanes in relation to the stator, and a second component which represents deformations which are caused by different elements of the rotor vanes. The method comprises a step of re-sampling the input signal in order to obtain a re-sampled input signal comprising a predefined whole number of samples per revolution of the turbomachine rotor. The method also comprises a step of processing the re-sampled input signal, comprising: filtering the re-sampled input signal, making it possible to acquire a filtered input signal in which the second component is attenuated, and separating the filtered input signal into a plurality of third components, each third component representing a contribution to the deformation caused by a respective associated vane. The method also comprises a step of detecting, in a third component, contact between the vane associated with the third component and the stator.

IPC Classes  ?

  • G01M 15/14 - Testing gas-turbine engines or jet-propulsion engines
  • F01D 21/00 - Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for

98.

Solution for manufacturing a one-piece bladed disc

      
Application Number 17783226
Grant Number 11964326
Status In Force
Filing Date 2020-12-10
First Publication Date 2023-01-19
Grant Date 2024-04-23
Owner SAFRAN (France)
Inventor Sallot, Pierre Jean

Abstract

A method for manufacturing an integrally formed bladed disk of a turbomachine, includes manufacturing a plurality of blades, the blades including a root and a profiled portion; and spark plasma sintering the blades with a metal powder, the blades being angularly distributed over a contour of an annular spark plasma sintering mold, the root of the blades being embedded into the metal powder, the profiled portion of the blades protruding from the metal powder radially outwardly.

IPC Classes  ?

  • B22F 5/04 - Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product of turbine blades
  • B22F 3/105 - Sintering only by using electric current, laser radiation or plasma
  • B22F 5/00 - Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product
  • B22F 7/06 - Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting of composite workpieces or articles from parts, e.g. to form tipped tools
  • F01D 5/30 - Fixing blades to rotors; Blade roots

99.

NICKEL-BASED SUPERALLOY

      
Application Number 17781596
Status Pending
Filing Date 2020-12-09
First Publication Date 2023-01-12
Owner SAFRAN (France)
Inventor
  • Rouffie, Anne-Laure
  • Franchet, Jean-Michel Patrick Maurice
  • Locq, Didier

Abstract

A Nickel-based superalloy, whose composition includes, in percent by weight of the total composition: Chromium: 10.0-11.25; Cobalt: 11.2-13.7; Molybdenum: 3.1-3.8; Tungsten: 3.1-3.8; Aluminium: 2.9-3.5; Titanium: 4.6-5.6; Niobium: 1.9-2.3; Hafnium: 0.25-0.35; Zirconium: 0.040-0.060; Carbon: 0.010-0.030; Boron: 0.01-0.030; Nickel: remainder as well as unavoidable impurities; the composition being free of tantalum.

IPC Classes  ?

  • C22C 19/05 - Alloys based on nickel or cobalt based on nickel with chromium
  • C22C 1/04 - Making non-ferrous alloys by powder metallurgy
  • 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

100.

FLUX BARRIER ELECTRIC MACHINE WITH SUPERCONDUCTING INDUCED ELEMENT AND INDUCTOR

      
Application Number 17782518
Status Pending
Filing Date 2020-12-01
First Publication Date 2023-01-05
Owner
  • SAFRAN (France)
  • UNIVERSITE DE LORRAINE (France)
Inventor
  • Ayat, Sabrina Siham
  • Colle, Alexandre
  • Biaujaud, Rémy

Abstract

A superconducting flux barrier electric motor, including at least one induced element and at least one conductor, one of the armature or the inductor housing at least one rotor and at least one superconducting induction coil, and the other including at least one arrangement of the electromagnetic coils coaxial with the superconducting induction coil the rotor comprising superconducting pellets mounted radially inside the superconducting coil on an axis of rotation of the motor, where the electromagnetic coils are made of superconducting material and the induced element and the inductor are arranged in an assembly forming a cooling chamber provided with specific cooling means for the superconducting elements of the induced element and the inductor.

IPC Classes  ?

  • H02K 55/00 - Dynamo-electric machines having windings operating at cryogenic temperatures
  • H01F 6/06 - Coils, e.g. winding, insulating, terminating or casing arrangements therefor
  • H02K 9/00 - Arrangements for cooling or ventilating
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