Patents Assigned to SAFRAN
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Publication number: 20230406780Abstract: Method for manufacturing a turbomachine blade made of ceramic-matrix composite material comprising an airfoil and a platform, producing a first fibrous preform, the first fibrous preform forming an airfoil preform, producing a second fibrous preform comprising a housing, the second fibrous preform forming a platform preform, producing a strand of ceramic fibers, consolidating the fibrous preforms and the strand of ceramic fibers to form consolidated preforms and a consolidated strand, assembling the consolidated preforms by engagement and cooperation of the first consolidated preform in the housing, the consolidated strand being interposed between the first consolidated preform and the second consolidated perform, co-densifying the assembly to form the turbomachine blade.Type: ApplicationFiled: October 27, 2021Publication date: December 21, 2023Applicant: SAFRAN CERAMICSInventor: Eric CONETE
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Publication number: 20230408552Abstract: Current sensor comprising: one pair, of identical electrical coils with superparamagnetic cores and surrounded by a common shielding braid; a direct current excitation means configured to make a direct current flow in at least one of the coils of the pair of coils and a means of adjusting an intensity of the direct current; a first alternating current excitation means configured to make an alternating current flow at a first frequency in the coils of the pair that the direct current flows through; a second alternating current excitation means configured to make an alternating current flow at a second frequency greater than the first frequency in the two coils of the pair of coils; a means of measuring an electromotive force of the Néel Effect® type at the terminals of the two coils of the pair.Type: ApplicationFiled: December 7, 2021Publication date: December 21, 2023Applicant: SAFRAN ELECTRICAL & POWERInventor: Lionel CIMA
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Publication number: 20230408567Abstract: A method for diagnosing an engine control unit of an aircraft uses a device having an autonomous and mobile electronic diagnostic unit and connecting means for connecting the unit to an engine control unit of an aircraft. The connecting means advantageously includes a single connection cable.Type: ApplicationFiled: October 4, 2021Publication date: December 21, 2023Applicant: SAFRAN AIRCRAFT ENGINESInventors: Yvan Jean-René BATTUT, Gwenael Thierry ESTEVE, Mathieu Jean Jacques SANTIN
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Publication number: 20230407797Abstract: An aircraft dual-flow turbine engine assembly includes: an internal shroud for externally delimiting a primary flow path of the turbine engine gases; an external shroud for internally delimiting a secondary flow path of the turbine engine gas; and at least one air discharge duct extending between the internal shroud and the external shroud, the air discharge duct opening into the secondary flow path through an outlet orifice equipped with discharge fins. At least some of the discharge fins are movably mounted so as to be able to be incidence-control between a propulsion position, and a reverse thrust position.Type: ApplicationFiled: November 2, 2021Publication date: December 21, 2023Applicant: SAFRAN AIRCRAFT ENGINESInventors: Eva Julie LEBEAULT, Philippe Gérard CHANEZ
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Publication number: 20230407765Abstract: Lubrication module for at least one lubrication station of a turbomachine, the lubrication module comprising at least one positive displacement pump including a pump body delimiting a main chamber configured to be in fluid communication with a main lubrication circuit and an auxiliary chamber configured to be in fluid communication with an auxiliary lubrication circuit, and a piston movably mounted in the pump body between an inactive configuration and an active configuration, the piston being configured to perform, in the active configuration, a pumping movement between a top dead center and a bottom dead center by cooperation with a cam of a shaft of the turbomachine and, in the inactive configuration, not to cooperate with the cam of the shaft of the turbomachine, the positive displacement pump including a return element configured to return the piston to the active configuration.Type: ApplicationFiled: June 16, 2023Publication date: December 21, 2023Applicant: SAFRAN TRANSMISSION SYSTEMSInventor: Abdallah BADIDI
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Publication number: 20230407791Abstract: 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.Type: ApplicationFiled: October 7, 2021Publication date: December 21, 2023Applicant: SAFRANInventors: Ephraïm TOUBIANA, Fabien DESARNAUD, Frédéric LAURENSAN
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Patent number: 11846234Abstract: 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.Type: GrantFiled: May 27, 2021Date of Patent: December 19, 2023Assignee: SAFRANInventors: Thierry Sibilli, Sarah Rebholz
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Patent number: 11846206Abstract: A turbine vane of a turbine engine is described. The turbine vane includes a blade and a root. The root includes a stilt having lateral flanks with a curvilinear profile. The stilt includes a frangible zone suitable for undergoing a breakage of the stilt if radial forces higher than a threshold are exerted on the vane, in particular centrifugal forces during an overspeed state of the turbine. The frangible zone includes at least one oblong frangibility recess formed on at least one of the lateral flanks of the stilt, the oblong recess extending in an axial direction of the stilt along a longitudinal axis parallel to or included in a minimum cross-sectional plane which contains a minimum cross-section of the stilt.Type: GrantFiled: May 18, 2020Date of Patent: December 19, 2023Assignee: SAFRAN HELICOPTER ENGINESInventor: Matthieu Claude Jean Denaux
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Patent number: 11846200Abstract: A device for centring and rotationally guiding a turbomachine shaft includes a rolling-element bearing outer ring; a bearing support having a radially inner annular surface surrounding the outer ring; a connection structure connecting the outer ring to the bearing support and including an elastically deformable structure; a first cavity formed between the radially inner annular surface and the outer ring to receive a first damping fluid film; at least one second cavity formed between the bearing support and the connection structure which is arranged radially outside the radially inner annular surface to receive a second respective damping fluid film. Such an arrangement allows for the coexistence of damping fluid films having very different damping properties.Type: GrantFiled: January 17, 2020Date of Patent: December 19, 2023Assignee: SAFRAN AIRCRAFT ENGINESInventors: Julien Fabien Patrick Becoulet, Alexandre Jean-Marie Tan-Kim
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Patent number: 11849373Abstract: A central communication unit (13), comprising: transmitter means arranged to transmit a single global downlink frame (17) addressed to all of the subscriber communication units, the global downlink frame comprising a plurality of data packets, each addressed to a respective one of the subscriber communication units, the global downlink frame supplying a common reference time so that, after receiving the global downlink frame (17), each subscriber communication unit can start transmitting an uplink frame (18) at the end of a waiting interval starting at the common reference time and having a duration equal to a respective waiting duration that is associated with said subscriber communication unit; and receiver means arranged to receive in succession the uplink frames (18) transmitted by each of the subscriber communication units.Type: GrantFiled: July 16, 2021Date of Patent: December 19, 2023Assignee: SAFRAN ELECTRONICS & DEFENSEInventors: Patrice Toillon, Thiebault Jeandon, Cédric Moreau
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Patent number: 11846513Abstract: A path is defined to be followed by a vehicle in an environment represented by a graph of nodes connected by edges. Each node represents the vehicle's position. Each edge between two nodes indicates a transition cost between the two nodes. An instance of the graph, which is represented by a start node, a destination node and mandatory nodes through which the vehicle must pass, is obtained. An initial order of travel through the mandatory nodes is obtained by applying a procedure, using a graph convolutional neural network, adapted to the graph, to the instance. A procedure of local optimisation of the mandatory nodes is executed in order to obtain an optimised order. A path for the instance is defined to be resolved: from the optimised order and for each pair of nodes of the instance to be resolved, from a shortest path between the nodes of the pair.Type: GrantFiled: April 9, 2020Date of Patent: December 19, 2023Assignee: SAFRAN ELECTRONICS & DEFENSEInventor: Kevin Osanlou
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Patent number: 11846420Abstract: A combustion chamber for a turbomachine including an annular casing delimiting an inner volume of the combustion chamber and provided with a chimney extending to the outside of the inner volume and delimiting a passage for a penetrating part, and a bushing mounted floating on the chimney, further includes: a main air collection chamber open to the upstream arranged facing the downstream portion of the chimney; and a through-opening of the annular casing, connecting the inner volume to the main air collection chamber. The air collected by the main air collection chamber is injected into the inner volume via the through-opening and can cool an annular casing zone downstream of the chimney.Type: GrantFiled: May 12, 2020Date of Patent: December 19, 2023Assignee: SAFRAN AIRCRAFT ENGINESInventors: Julien Marc Matthieu Leparoux, Christophe Pieussergues
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Patent number: 11845483Abstract: A disclosed controller is configured with logic that, when executed, performs actions to extend landing gear of a maglev vehicle. The actions include receiving a height control target value and transitioning between a standby control state and an active control state. The controller maintains the landing gear in a fixed position when the controller is in the standby control state, and the controller controls extension and retraction of the landing gear according to the height control target value when the controller is in the active control state.Type: GrantFiled: March 29, 2021Date of Patent: December 19, 2023Assignees: SAFRAN LANDING SYSTEMS CANADA INC., SAFRAN LANDING SYSTEMSInventors: Andrew Michael Ellis, Graeme Peter Arthur Klim, Thibaud Mazoue
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Patent number: 11846198Abstract: A turbomachine, particularly for a rotary-wing aircraft, including a gas generator provided with a rotary shaft, a first reversible electric machine, a power turbine rotationally driven by a stream of gas generated by the gas generator, at least one accessory from among an oil pump and a fuel pump, an accessory gearbox comprising a gear train configured to drive said at least one accessory, and a second electric machine. The second electric machine is reversible, said first electric machine is mechanically coupled to the gas generator, the accessory gearbox and the second electric machine are mechanically coupled to the power turbine, and the turbomachine is devoid of any kinematic coupling between the gear train of the accessory gearbox and the shaft of the gas generator.Type: GrantFiled: November 12, 2021Date of Patent: December 19, 2023Assignee: SAFRAN HELICOPTER ENGINESInventors: Loïs Pierre Denis Vive, Olivier Bedrine, Thomas Drouin
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Patent number: 11846250Abstract: A turbofan aircraft propulsion assembly includes a retractable heat exchanger. The heat exchanger can be deployed in a secondary flow path of the propulsion assembly so as to cool a fluid circulating in a circuit of a transfer module of the heat exchanger using a secondary flow circulating in the secondary flow path.Type: GrantFiled: March 19, 2021Date of Patent: December 19, 2023Assignee: SAFRAN AIRCRAFT ENGINESInventors: Alexandre Gérard François Couilleaux, Mathieu Lasne
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Patent number: 11845555Abstract: An on-board device for a vehicle, preferably a galley or a bar for an airplane, has at least one visible side wall and at least one paneling for partially or completely concealing a work area of the on-board device. The paneling is adjustable between at least two configurations. The paneling forms or covers at least part of the side wall in a first configuration and conceals the work area partially or completely in a second configuration.Type: GrantFiled: June 22, 2018Date of Patent: December 19, 2023Assignee: Safran Cabin Germany GmbHInventors: Dennis Hausner, Samuel Klassen, Nathalie Christian
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Patent number: 11846194Abstract: A set of compression stage(s) of a turbomachine, forming an annular fluid passage and comprising at least one annular stator platform and/or at least one annular rotor platform having an outer longitudinal profile inclined (ISi/IRi) inwards and upstream with respect to a nominal profile of the fluid stream, where the inclination (ISi/IRi) of the outer longitudinal profile of the or each of the annular platforms, relative to the nominal profile of the fluid stream, oscillates along the circumference of the annular platform or platforms, between a maximum value in front of the blades of the annular platform and a minimum value between each pair of adjacent blades of the annular platform.Type: GrantFiled: January 22, 2021Date of Patent: December 19, 2023Assignee: SAFRAN AIRCRAFT ENGINESInventors: Michaël Franck Antoine Schvallinger, Mickael Cavarec
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Patent number: 11840029Abstract: The present disclosure concerns a method for manufacturing a composite panel including a cellular central core interposed between two skins. The manufacturing method includes the steps of manufacture of an element with a cellular structure comprising a cellular core structure interposed between two layers of structural plies intended to form the skins, positioning of the element with a cellular structure within a mold, formation of drains on either side of the cellular core structure, infusion of the element with a cellular structure so as to impregnate it with a resin, carrying out a draining of the resin through the drains in the element with a cellular structure during the infusion step, the drains having a geometry configured to provide draining, and polymerization of the impregnated element with a cellular structure to form the composite panel.Type: GrantFiled: January 11, 2021Date of Patent: December 12, 2023Assignee: Safran NacellesInventors: Clément Rolland, Jean Baptiste Delarue, Jean Jacques Thomas, Vianney Hus, Mathieu Preau, Alain Roussel
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Patent number: 11840994Abstract: The fuel injection conduits in a multipoint device surrounding a so-called pilot central injection device include tubes of circumferential orientation. By separating the injection conduits from each other, it is possible to attribute to them different head losses which compensate the differences in length that the fuel has to travel: a uniform flow of fuel may be hoped for, for each of the injection holes. The tubes are individual but joined to form a crown that is unitary or composed of two almost symmetrical unitary portions, which lends itself well to manufacture by addition of material.Type: GrantFiled: July 22, 2019Date of Patent: December 12, 2023Assignee: SAFRAN AIRCRAFT ENGINESInventors: Sébastien Alain Christophe Bourgois, Romain Nicolas Lunel, Haris Musaefendic
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Patent number: 11841140Abstract: A pre-vaporisation tube for a turbine engine combustion chamber includes a main body ROOM defining a first inner duct configured to have an injector mounted therein. The tube includes a first end attached to a wall of the chamber, and at least two end pieces are arranged at a second end of the body and define second inner ducts. The end pieces include first portions and second portions, respectively. The second portions each include two coaxial cylindrical walls which are inner and outer coaxial cylindrical walls, respectively, and which define an annular cavity therebetween. The inner wall defines an inner passage and has first openings for fluid communication between the passage and the annular cavity.Type: GrantFiled: October 5, 2020Date of Patent: December 12, 2023Assignee: SAFRAN HELICOPTER ENGINESInventors: Thomas Jean Olivier Lederlin, Christophe Laurent, Guillaume Gerard Joel Mauries