Patents Assigned to SAFRAN POWER UNITS
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Patent number: 12196097Abstract: A lubrication reservoir for a turbine engine for an aircraft or self-propelled flying machine, comprising a suction strainer in a lower part of the chamber, and at least one degassing device and at least one vent in an upper part. The reservoir is wherein, in order to make it possible to supply the strainer and prohibit lubricant from intruding into the at least one vent, it includes at least one first partition that separates the lower part from the upper part and is pierced with calibrated holes, two vents arranged on either side of a vertical median plane of the chamber and two vent ducts which extend into the upper part below the degassing device, each duct comprising a bend and having the bend located on the other side of the median plane with respect to the inlet thereof.Type: GrantFiled: June 13, 2021Date of Patent: January 14, 2025Assignee: SAFRAN POWER UNITSInventors: Victor Georges Maurice Lhomme, Franck Jean-Louis Galibert, Gilles Aime Yann Guyader, Claire Madeleine Martin
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Publication number: 20240282986Abstract: Disclosed is a method for controlling a pressure regulating valve (6) for regulating the internal pressure (Pint) of a fluid circuit (3) in an electrochemical device (2), said fluid circuit (3) being fed by a compressor (4) drawing air at an external pressure (Pext) and compressing same at the internal pressure (Pint) according to a compression ratio (A); said method comprises a step of measuring the external pressure (Pext), determining an internal pressure set point (Pint*) on the basis of the external pressure (Pext) measured and the compression range (B), so as to promote overall efficiency (R1) of the electrochemical device (2) and the compressor (4) according to the internal pressure (Pint) and the compression ratio (A), and a step of controlling the pressure regulating valve (6) so as to reach the internal pressure set point (Pint*).Type: ApplicationFiled: May 31, 2022Publication date: August 22, 2024Applicant: SAFRAN POWER UNITSInventors: Kilian Frank, Claude BERNARD, Robin Jacques, Marie VIALET, Olivier Rafaël, René CRASSOUS, Rémi André, Armand STEPHAN
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Patent number: 12040519Abstract: A fuel cell comprising a stack which comprises a plurality of cells, each cell comprising a plurality of fluid flow openings aligned in parallel to form a plurality of fluid flow lines in the stack, two end plates placed at the ends of the stack and at least one traction member connecting the end plates to each other in order to compress the stack, the traction member being mounted in a fluid flow line of the stack.Type: GrantFiled: December 4, 2019Date of Patent: July 16, 2024Assignee: SAFRAN POWER UNITSInventors: Romain Quinton, Jean-Baptiste Jollys, Théophile Horde
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Patent number: 12027738Abstract: The invention relates to a fuel cell comprising a plurality of modules mounted in series with one another so as to form a peripheral structure, each module comprising two end members and a stack of electrochemical cells mounted between two end members, each end member including a mounting face in contact with one of the ends of a stack and an interface face in contact with another interface face of another end member, the mounting face and the interface face being angularly spaced apart by an angle (?) which is between 0.5° and 60°.Type: GrantFiled: December 9, 2019Date of Patent: July 2, 2024Assignee: SAFRAN POWER UNITSInventors: Romain Quinton, Jean-Baptiste Jollys, Théophile Horde
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Publication number: 20240200493Abstract: The invention relates to an acoustic insulation assembly for an auxiliary power unit having a centrifugal compressor (1), comprising a ring-shaped casing (8) for an air inlet (3) and comprising a plurality of reinforcing arms (9) connecting its inner walls, a plurality of removable mechanical acoustic insulation parts (10), each mechanical part (10) being ring-shaped and comprising attachment means (11) intended to engage with the casing (8), such that the mechanical part (10) and the flow surface of the casing (8), defined by a pair of reinforcing arms (9), overlie one another.Type: ApplicationFiled: June 30, 2022Publication date: June 20, 2024Applicant: SAFRAN POWER UNITSInventors: Laurent Stéphane Tardy, Jaime Georges Paul Culla
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Publication number: 20240175397Abstract: A gas turbine of an aircraft includes start-up system configured to drive a shaft of the gas turbine in rotation. The start-up system includes a control system and a brushless asynchronous electric machine and is supplied with a DC voltage. A method for starting the gas turbine includes the steps of converting the DC voltage into a three-phase voltage control system based on a first value representative of a rotational speed of a rotor of the electric machine and on a second value representative of a ratio of a determined target torque of the electric machine, suitable for driving the rotation of a shaft of the gas turbine at a determined speed, to the maximum theoretical torque that the electric machine is able to produce at the determined rotational speed of the rotor.Type: ApplicationFiled: March 30, 2022Publication date: May 30, 2024Applicant: SAFRAN POWER UNITSInventor: Marc Daniel TUNZINI
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Patent number: 11940008Abstract: Rolling-element bearing for a turbomachine of an aircraft, comprising an inner ring (3) defining a first raceway (112), and an outer ring (4) defining a second raceway (124), characterized in that the bearing has at least one loop circuit (21, 22) for forced recirculation of lubricant, this loop circuit comprising a first recirculation circuit (21) comprising at least one lubricant inlet (1200) located on the second raceway (124), and connected by at least one duct (120, 166) created in the outer ring (4) to at least one lubricant outlet (1661) which discharges into a second recirculation circuit (22) of the loop circuit (21, 22), this second recirculation circuit (22) comprising at least one duct (152, 1134, 1136; 1135, 1136) created in the inner ring (3).Type: GrantFiled: July 9, 2020Date of Patent: March 26, 2024Assignee: SAFRAN POWER UNITSInventors: Serge Marie Gabriel Cot, Jean-Paul Salvador Lopez, Stephane Chevalier
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Patent number: 11891907Abstract: A turbogenerator (1) for an aircraft (2) comprising: a turboshaft engine (3); an electric generator (4) comprising a rotor (5) driven mechanically by the turboshaft engine (3) and a stator (6) supported by a housing (7) of the electric generator (4); characterized in that the turbogenerator (1) comprises a static separator (8) for separating an air/oil mixture coming from the turboshaft engine (3), the static separator (8) being positioned around the housing (7) of the electric generator (4).Type: GrantFiled: December 18, 2020Date of Patent: February 6, 2024Assignees: SAFRAN HELICOPTER ENGINES, SAFRAN POWER UNITSInventors: Camel Serghine, Denis Antoine Julien Real
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Publication number: 20240002059Abstract: An architecture for supplying air to a high-pressure compressor (140) of an auxiliary gas generator (14) from a pressurized cabin (12) of an aircraft, comprising: a load compressor (16, 52) rotationally driven by a common rotation shaft (146) providing a mechanical coupling between the high-pressure compressor and a high-pressure turbine (144) of the auxiliary gas generator and supplied by an outside air intake (18, 58); a first regulation valve (22) assembled at the outlet of the load compressor to control all or part of the air flow delivered by the load compressor; a second regulation valve (22) assembled at the outlet of the pressurized cabin to control the air flow drawn from inside the pressurized cabin; a mixer (24) receiving the outputs of the first and second regulation valves to add the air drawn from inside the pressurized cabin to all or part of the air delivered by the load compressor; and a third regulation valve (26) assembled at the outlet of the mixer to control the air flow injected into theType: ApplicationFiled: November 9, 2021Publication date: January 4, 2024Applicant: SAFRAN POWER UNITSInventors: Bernard BLANC, Damien Jacques Arthur BONHOMME
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Patent number: 11827374Abstract: In the field of multi-rotor rotary-wing aircraft a propulsion system for such an aircraft includes a reconfigurable electric network for supplying the electric motors driving the rotors. The system includes: a supply source, a supply bus connected to the supply source, at least four drive units each including an electric motor and its control circuit, and an electrical ring network including: an electrical line which is interrupted at each drive unit and whose ends are connected to the supply bus, and, for each drive unit, a first switch and a second switch that are connected between the control circuit and the electrical line, on either side of the interruption.Type: GrantFiled: March 25, 2019Date of Patent: November 28, 2023Assignees: SAFRAN, SAFRAN ELECTRICAL & POWER, SAFRAN HELICOPTER ENGINES, SAFRAN POWER UNITS, SAFRAN ELECTRONICS & DEFENSEInventors: Thomas Klonowski, Thomas Barraco, Camel Serghine
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Publication number: 20230378488Abstract: A fuel cell comprising an upper plate and a lower plate, a stack of energy cells, the stack being disposed between the upper plate and the lower plate, the stack being divided into a plurality of energy cell stages, a plurality of collectors separating each energy cell stage, three inlet vents extending from the lower plate to the upper plate, over the entire height of the stack of energy cells, the three inlet vents being configured to respectively provide the energy cells with heat transfer fluid, comburent fluid and liquid fuel, and a movable piston is disposed in each of the inlet vents, each piston being configured so that its position in the inlet vent selectively opens one or more of the fluid ducts of one or more energy cell stages, and wherein each piston is driven independently of the other pistons.Type: ApplicationFiled: October 7, 2021Publication date: November 23, 2023Applicant: SAFRAN POWER UNITSInventors: Romain QUINTON, Théophile HORDE, Rémi André Armand STEPHAN
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Publication number: 20230317979Abstract: Fuel cell including a stack of membrane/electrodes assemblies, an inlet end plate and an outlet end plate, n intermediate plates disposed in the stack between the inlet and outlet end plates to form n+1 sub-stacks of the stack, n being greater than or equal to 1. The fuel cell may include ducts for circulating a heat transfer fluid, an oxidant and a fuel passing in the inlet and outlet end plates and the n intermediate plates, valves that may control the heat transfer fluid in the circulation ducts, and valves that may control the heat transfer fluid, the oxidant, and the fuel in the circulation ducts of the n intermediate plates and may be configured to allow circulation of the heat transfer fluid, the oxidant, and the fuel in m sub-stacks of the stack, m being greater than or equal to 1 and less than or equal to n.Type: ApplicationFiled: July 28, 2021Publication date: October 5, 2023Applicant: SAFRAN POWER UNITSInventors: Rémi André Armand STEPHAN, Théophile HORDE, Loïc Pierre Michel RIOS
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Patent number: 11738882Abstract: An aircraft auxiliary power unit is equipped with a charging compressor. A method determines a surge parameter indicative of a risk that the charging compressor will display the phenomenon known as surge. A method and a system control a relief valve of this charging compressor. The method for determining the surge parameter includes calculating this surge parameter Ppomp as being the sum of a first term T1 and of a second term T2, the first term T1 being calculated on the basis of a first pressure P1 measured downstream of a diffuser of the charging compressor, and of a second pressure P2 measured upstream of the diffuser, the second term T2 being calculated on the basis of a third pressure P3 measured upstream of the diffuser and of an ambient pressure Psamb indicative of a pressure of an ambient environment.Type: GrantFiled: July 31, 2020Date of Patent: August 29, 2023Assignee: SAFRAN POWER UNITSInventors: David Francis Pierre Ormieres, Louis Jean-Paul Fabien Perrot-Minot
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Publication number: 20230258129Abstract: Hybrid turbomachine comprising an electric generator, a gas generator equipped with an air inlet and with an exhaust and an acoustic monitoring system comprising a control unit and a plurality of loudspeakers. At least a first loudspeaker is disposed on the electric generator, and/or at least a second loudspeaker is disposed on the air inlet of the gas generator, and/or at least a third loudspeaker is disposed on the exhaust of the gas generator. The control unit of the acoustic monitoring system is mounted on the electric generator and is configured to make an AC-DC electrical conversion of the electromotive force of the electric generator into an adjustable DC voltage intended to be distributed to loads or to energy storage means.Type: ApplicationFiled: September 3, 2021Publication date: August 17, 2023Applicants: SAFRAN HELICOPTER ENGINES, SAFRAN ELECTRICAL & POWER, SAFRAN POWER UNITSInventors: Romain Jean Gilbert THIRIET, Eric Jean-Louis BOUTY, Denis Antoine Julien REAL, Valéry CHAU
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Publication number: 20230021361Abstract: An auxiliary power unit, in particular for an aircraft, includes a gas generator and an electric generator. The electric generator has an input shaft that is connected to an output shaft of the gas generator. The auxiliary power unit also has an accessories housing directly connected to a rotor shaft of the electric generator, wherein the electric generator is interposed between the gas generator and the accessories housing.Type: ApplicationFiled: December 7, 2020Publication date: January 26, 2023Applicant: SAFRAN POWER UNITSInventors: Marc Daniel TUNZINI, Denis Antoine Julien REAL
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Patent number: 11489176Abstract: An assembly for producing energy may include a fuel cell, a fluidic cell circuit configured to receive a first heat-transfer fluid and arranged at least partially around the fuel cell, a reversible thermodynamic system configured to alternatively: (i) evacuate the thermal energy produced by the fuel cell and transform it into mechanical energy through the first heat-transfer fluid, and (ii) input thermal energy to the fuel cell through the first heat-transfer fluid, wherein the thermodynamic system includes: (a) a fluidic thermodynamic circuit to receive a second heat-transfer fluid; (b) a first exchanger to exchange thermal energy between the fluidic thermodynamic circuit and the fluidic cell circuit; and (c) a second exchanger configured to exchange thermal energy between the fluidic thermodynamic circuit and an external source.Type: GrantFiled: December 27, 2018Date of Patent: November 1, 2022Assignees: 1). COMMISSARIAT A L'ENERGIE ATOMIQUE ET AUX ENERGIES ALTERNATIVES, SAFRAN POWER UNITSInventors: Nicolas Tauveron, Benjamin Boillot, Jean-Baptiste Jollys
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Patent number: 11465754Abstract: A pressurized air supply unit (1; 1?) for an aircraft, comprising: a load compressor (30; 30?) configured to supply pressurized air (3), the load compressor (30; 30?) having a compressor shaft (23; 23?); and a drive portion (10) configured to supply power via an output shaft (20); the pressurized air supply unit (1; 1) being characterized in that it comprises: a gearbox (50); an electric motor (40), the electric motor (40) being coupled to said compressor shaft (23; 23?) via the gearbox (50); and a coupling system (25) configured to enable the output shaft (20) to drive the compressor shaft (23; 23?) and to prevent the compressor shaft (23; 23?) from driving the output shaft (20), and in that the output shaft (20) and the compressor shaft (23) lie on the same axis.Type: GrantFiled: March 22, 2017Date of Patent: October 11, 2022Assignee: SAFRAN POWER UNITSInventors: Fabien Silet, Laurent Batailler
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Publication number: 20220274716Abstract: An aircraft auxiliary power unit is equipped with a charging compressor. A method determines a surge parameter indicative of a risk that the charging compressor will display the phenomenon known as surge. A method and a system control a relief valve of this charging compressor. The method for determining the surge parameter includes calculating this surge parameter Ppomp as being the sum of a first term T1 and of a second term T2, the first term T1 being calculated on the basis of a first pressure P1 measured downstream of a diffuser of the charging compressor, and of a second pressure P2 measured upstream of the diffuser, the second term T2 being calculated on the basis of a third pressure P3 measured upstream of the diffuser and of an ambient pressure Psamb indicative of a pressure of an ambient environment.Type: ApplicationFiled: July 31, 2020Publication date: September 1, 2022Applicant: SAFRAN POWER UNITSInventors: David Francis Pierre ORMIERES, Louis Jean-Paul Fabien PERROT-MINOT
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Patent number: 11396833Abstract: An oil storage and filtration system for an engine unit includes an on/off valve that defines an operating phase when receiving supply air and in an on position and a standby phase when in an off position or not receiving the supply air. The system also includes a fill/drain valve that defines a drain state and a fill state which respectively correspond to emptying and filling oil from/into the engine unit. The system also includes a control valve, a pressure/vacuum valve, and a storage tank. The storage tank stores oil in a pressurized condition during the fill state, a vacuum condition during the drain state, and an atmospheric condition during the standby phase. The also includes a vacuum generator in fluid communication with the storage tank during the drain state and fluidly isolated from the storage tank during the fill state.Type: GrantFiled: January 24, 2020Date of Patent: July 26, 2022Assignee: SAFRAN POWER UNITSInventor: Mark Scudder
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Publication number: 20220213842Abstract: A propulsion assembly for aircraft includes a single-shaft engine turbomachine including a combustion chamber and a rotatably mounted shaft that turns at a turbomachine rating; an electrical generator coupled to the shaft; and a control system. The control system includes a fuel pump that brings fuel into the combustion chamber at a fuel flow rate which is a direct function of an ambient pressure and of the turbomachine rating, and power electronics that are coupled to the electrical generator and that control an electrical power drawn off the electrical generator so as to attain a target turbomachine rating.Type: ApplicationFiled: July 3, 2020Publication date: July 7, 2022Applicants: SAFRAN HELICOPTER ENGINES, SAFRAN POWER UNITSInventors: Fabien MERCIER-CALVAIRAC, Patrick MARCONI, Denis Antoine Julien REAL