Patents Assigned to SAFRAN
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Publication number: 20240097548Abstract: 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).Type: ApplicationFiled: January 18, 2022Publication date: March 21, 2024Applicants: SAFRAN, UNIVERSITE DE LORRAINEInventors: Sabrina Siham AYAT, Rémi Luc Stéphane DORGET, Benjamin DAGUSE
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METHOD FOR OBTAINING A PRODUCT MADE OF TITANIUM ALLOY OR A TITANIUM-ALUMINIUM INTERMETALLIC COMPOUND
Publication number: 20240091850Abstract: 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.Type: ApplicationFiled: December 2, 2021Publication date: March 21, 2024Applicant: SAFRANInventor: Pierre Jean SALLOT -
Publication number: 20240097549Abstract: 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).Type: ApplicationFiled: January 13, 2022Publication date: March 21, 2024Applicants: SAFRAN, UNIVERSITE DE LORRAINEInventors: Sabrina Siham AYAT, Rémi Luc Stéphane DORGET, Benjamin DAGUSE
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Publication number: 20240093773Abstract: An accessory gearbox houses at least one gear train with a series of pinions. The casing has two substantially flat and opposite parallel side walls between which are mounted support shafts for each of the pinions, each of which receives accessories, and which define in the enclosure an internal volume surrounding a shaft supporting at least one hybridization pinion. The gearbox receives at least one electric machine having a rotor and a stator, wherein the rotor of the electric machine is supported by the shaft supporting the hybridization pinion of the gear train, and the stator extends around the rotor in the internal volume.Type: ApplicationFiled: September 20, 2023Publication date: March 21, 2024Applicant: SAFRAN TRANSMISSION SYSTEMSInventors: Clément FALGUIERE, Clément Romain Aimé CADET, Florian Pierre-Yves CHAPUT, Raphaël Clément Stéphane MARTIN
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Publication number: 20240094089Abstract: 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.Type: ApplicationFiled: January 19, 2022Publication date: March 21, 2024Applicant: SAFRANInventors: Amadou ASSOUMANE, Dany ABBOUD, Mohammed EL BADAOUI
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Publication number: 20240092497Abstract: Propulsion system (2) for a helicopter (1) comprising a main engine (9), a main rotor (3), a main gearbox (4) including an output mechanically connected to the main rotor (3), a reduction gearbox (13) mechanically coupled between the main engine (9) and a first input of the main gearbox (4), and an assistance device (10). The assistance device (10) comprises a first electric machine mechanically coupled to the reduction gearbox (13) and configured to operate as an electric generator to take off energy produced by the main engine (9), and a second electric machine mechanically coupled to a second input of the main gearbox (4), the second electric machine being supplied with electrical power by the first electric machine and configured to operate as an electric motor to deliver additional mechanical power to the main gearbox (4).Type: ApplicationFiled: December 3, 2021Publication date: March 21, 2024Applicant: SAFRAN HELICOPTER ENGINESInventors: Romain Jean Gilbert THIRIET, Fabien MERCIER-CALVAIRAC, Stéphane Albert André DOUILLARD
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Publication number: 20240093343Abstract: 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 ?-?? 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 ?-?? phase and an average mass fraction of rhenium and/or ruthenium of less than 1%.Type: ApplicationFiled: October 8, 2020Publication date: March 21, 2024Applicant: SAFRANInventors: Amar SABOUNDJI, Fabrice CRABOS
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Publication number: 20240092480Abstract: A device for driving at least one wheel of an aircraft landing gear is provided. The device includes at least one wheel having a rim, an electric motor having a shaft, and a mechanical transmission system for mechanical transmission between the shaft of the motor and the rim. The mechanical transmission system includes a mechanical reduction gear. The mechanical reduction gear includes a sun gear secured in rotation to the shaft and having an external toothing, a stationary ring gear with internal toothing, a movable ring gear secured in rotation to the rim and having an internal toothing, and planet gears that are meshed with the sun gear and each have two external toothing meshed respectively with the toothing of the stationary and movable ring gears.Type: ApplicationFiled: September 14, 2023Publication date: March 21, 2024Applicant: SAFRAN TRANSMISSION SYSTEMSInventors: Maxime Fernandez, Yohan Douy, Loïc Francois, Boris Pierre Marcel Morelli, Jordane Emile André Peltier
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Patent number: 11933497Abstract: The invention relates to an air/fuel injection system for a turbomachine, comprising:—an injector comprising a duct and an injection nose, arranged inside said duct, which extends from upstream to downstream along a longitudinal axis;—a mixer device comprising a bowl comprising an annular inlet, forming the inlet of the mixer device, from which there extends a conical portion flared in the downstream direction, said mixer device being arranged downstream of the injection nose; the injection system being characterized in that the injector comprises an air-injection annulus extending from the duct and from which there extends a connection ring comprising a divergent portion, said ring being arranged externally around the annular inlet of the mixer device.Type: GrantFiled: November 24, 2020Date of Patent: March 19, 2024Assignee: SAFRAN AIRCRAFT ENGINESInventors: Romain Nicolas Lunel, Haris Musaefendic
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Patent number: 11932399Abstract: A sandwich panel for an aircraft turbojet nacelle includes an outer skin in contact with an air flow, an inner skin opposed to the outer skin, and an intermediate system comprising partitions connecting the inner and outer skins so as to form cells, the inner skin of at least one cell having at least one corrugation configured to allow the materials making up the sandwich panel to deform in the event of thermal variation.Type: GrantFiled: August 26, 2021Date of Patent: March 19, 2024Assignees: Safran Nacelles, Safran CeramicsInventors: Bertrand Desjoyeaux, Davi Silva De Vasconcellos, François Taillard, Florent Bouillon
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Patent number: 11932942Abstract: A process for depositing a coating on a continuous fibre of carbon or silicon carbide from a precursor of the coating, includes heating a segment of the fibre in the presence of the coating precursor in a microwave field so as to bring the surface of the segment to a temperature allowing the coating to form on the segment from the coating precursor, wherein the segment of fibre is in the presence of a supercritical phase of the precursor of the coating in the reactor and the coating is formed by supercritical phase chemical deposition in the reactor.Type: GrantFiled: June 16, 2022Date of Patent: March 19, 2024Assignees: SAFRAN CERAMICS, CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE, UNIVERSITE DE BORDEAUXInventors: Arnaud Delehouze, Eric Bouillon, Adrien Delcamp, Cédric Descamps
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Patent number: 11933230Abstract: An aircraft turbomachine having a longitudinal axis includes a high-pressure (HP) body, a low-pressure (LP) body, a fan, and a reduction gear having an epicyclic gear train. The turbomachine includes three modules: a first module having the LP turbine and the LP shaft, a second module having the LP compressor and a journal secured to the rotor of the LP compressor, and a third module having an input shaft of the reduction gear, this input shaft having an upstream end for coupling to a sun gear of the reduction gear and a downstream end comprising first splines that are oriented parallel to the axis and are configured to be engaged in second complementary splines of said second module.Type: GrantFiled: November 2, 2021Date of Patent: March 19, 2024Assignee: Safran Aircraft EnginesInventors: Paul Ghislain Albert Levisse, Olivier Belmonte
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Patent number: 11933224Abstract: The present invention relates to a fuel metering unit for an aircraft engine, comprising: —a metering member configured to receive a position control signal and to meter the feed of fuel to the engine depending on said position control; —a cutting member configured to cut the feed of fuel to the engine; and characterized in that the fuel metering unit also has a computer for protecting and cutting the engine, said protecting and cutting computer being configured to—detect an overspeeding state of the engine speed and—in response to the detection of an overspeeding state, to transmit a cutting control signal to a cutting control member contained in the cutting member.Type: GrantFiled: November 12, 2019Date of Patent: March 19, 2024Assignee: SAFRAN AIRCRAFT ENGINESInventors: Guilhem Alcide Auguste Foiret, Arnaud Bernard Clément Thomas Joudareff
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Patent number: 11933194Abstract: Fan or propeller vane (1) for an aircraft turbomachine, the vane being made from a composite material and comprising a blade (2) and a base (3), the base being formed by a longitudinal end (41) of a spar (4) which is formed by a fibrous reinforcement formed from threads woven in three dimensions and a portion (42) of which extends inside the blade (2), the blade (2) having an aerodynamic profile which is defined by a skin (5) which is formed by woven threads and which surrounds the portion of the spar, the spar (4) and the skin (5) being embedded in a polymerised resin, characterised in that the portion (42) of the spar comprises projecting longitudinal stiffening members (6) which together delimit spaces (8) for receiving longitudinal inserts (7) which are formed from a honeycomb material.Type: GrantFiled: December 17, 2020Date of Patent: March 19, 2024Assignee: SAFRAN AIRCRAFT ENGINESInventors: Vivien Mickael Courtier, Teddy Fixy, Clement Pierre Postec, Eddy Keomorakott Souryavongsa
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Patent number: 11933229Abstract: Speed reduction gear for an aircraft turbomachine. The reduction gear has a main axis and planet carrier having a cage and a cage carrier, a sun gear located in the cage and centred on the main axis, an annular row of planet gears arranged around the main axis and the sun gear and meshed with the sun gear, and a ring gear arranged around the axis and the cage and meshed with the planet gears. The cage and the cage carrier are connected to each other by connections whose bending flexibility is optimised.Type: GrantFiled: February 6, 2023Date of Patent: March 19, 2024Assignee: SAFRAN TRANSMISSION SYSTEMSInventors: Patrice Julien Ptaszynski, Antoine Jacques Marie Pennacino, Boris Pierre Marcel Morelli
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Patent number: 11932408Abstract: Series hybrid propulsion unit including a gas turbine driving a mechanical shaft of an electric generator having n output phases and supplying an AC busbar, and a system for monitoring the speed of the gas turbine, the AC busbar supplying a plurality of AC distribution channels each composed of an electric rectifier and a battery sharing the power required to supply a DC bus, the DC bus in turn supplying a plurality of propulsion sub-channels composed of electric inverters supplying, under the monitoring of a control module, motors driving thrusters, further including a battery charger for charging the battery from the DC bus, a power management module delivering a power reference for the electric generator, and a hybridization rate management module monitoring the voltage of the DC bus, the battery being directly connected on the DC bus via a passive component and the electric rectifier being a passive converter.Type: GrantFiled: September 2, 2019Date of Patent: March 19, 2024Assignee: SAFRANInventors: Jean-Philippe Hervé Salanne, Stéphane Petibon, Florent Rougier
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Patent number: 11932403Abstract: Described are tray tables having a shroud and a core assembly. The shroud may form an outer surface of the tray table. The core assembly may be within the shroud and may include a top sheet, a bottom sheet, and a honeycomb core. The honeycomb core may be between the top sheet and the bottom sheet. The honeycomb core may define a plurality of cells.Type: GrantFiled: January 10, 2022Date of Patent: March 19, 2024Assignee: Safran Seats USA LLCInventors: Gokul Ramarathnam, Reza Mansouri
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Patent number: 11933246Abstract: An aircraft turbojet engine extending along an X axis and comprising a blower configured to provide a reverse thrust and a nacelle comprising an air intake which comprises at least one deflection member movably mounted between a deployed position in which the deflection member projects from the inner wall or from the lip of the air intake in a radially inward direction of deployment facing the X axis or in a longitudinal direction of deployment with respect to the X axis, in order to allow a release of the reverse air flow from the inner wall to support the reverse thrust phase, and a retracted position in which the air intake has an aerodynamic profile so as to guide the internal air flow along the inner wall in order to support the thrust phase.Type: GrantFiled: April 8, 2020Date of Patent: March 19, 2024Assignee: SAFRAN AIRCRAFT ENGINESInventors: Daniel-Ciprian Mincu, Jean-Loïc Hervé Lecordix, Nicolas Joseph Sirvin, Frédéric Dautreppe, Anthony Binder, Eva Julie Lebeault
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Patent number: 11931770Abstract: A process for coating an aircraft turbomachine component with an erosion-resistant coating, includes depositing the erosion-resistant coating by hot powder-coating on an aircraft turbomachine component made of an organic-matrix composite material or of a metallic material, the erosion-resistant coating including a polyurethane or silicone polymer, the polymer having a glass transition temperature of less than or equal to ?30° C.Type: GrantFiled: April 21, 2020Date of Patent: March 19, 2024Assignee: SAFRAN AIRCRAFT ENGINESInventor: Mathieu Julien Charlas
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Patent number: 11933181Abstract: An abradable coating for a turbomachine part, includes a matrix made of a first metal material and particles made of a second metal material that are dispersed in the matrix, the first metal material having a melting temperature greater than 900° C., the second metal material having a melting temperature at least 50° C. lower than the melting temperature of the first metal material.Type: GrantFiled: May 17, 2022Date of Patent: March 19, 2024Assignee: SAFRAN AIRCRAFT ENGINESInventors: Philippe Charles Alain Le Biez, Nicolas Droz, Lisa Pin, Serge Georges Vladimir Selezneff