Patents Assigned to SAFRAN
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Patent number: 11698188Abstract: A flat-jet fuel injector for an aircraft turbine engine, comprising a body having a generally elongate shape having a longitudinal axis A, the body comprising a main pipe having a generally elongate shape having a longitudinal axis B substantially perpendicular to the longitudinal axis A, the two longitudinal ends of the main pipe being connected directly and respectively to longitudinal ends of two secondary pipes having a generally elongate shape having a longitudinal axis C at least substantially parallel to the longitudinal axis A, and being configured to form, respectively, two separate fuel flow inlets intended to meet substantially at the middle of the main pipe which comprises at least one ejection slot for ejecting the fuel jet, wherein at least one of the main and secondary pipes defines a flow area, at least one geometric parameter of which, such as the shape or a dimension, varies along the pipe and/or is different from the same geometric parameter defined by a flow area of another of the pipes.Type: GrantFiled: June 18, 2018Date of Patent: July 11, 2023Assignee: Safran Helicopter EnginesInventors: Denis Chanteloup, Thomas Lederlin, Guillaume Mauries, Simon Meilleurat
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Patent number: 11700297Abstract: A data loading device for loading data into computer processor units from a data source, the device comprising at least a first connector for connecting to the data source and provided with a PHY component, and a plurality of second connectors for connecting to the computer processor units and each provided with a respective PHY component, the first connector being connected to the second connectors by a first selector module in order to define a single down channel so as to transmit data from the first connector to each of the second connectors individually, and by a second selector module for defining a single up channel so as to transmit data in the opposite direction, the selector modules being arranged to be capable of connecting only one of the second connectors at a time to the first connector and the device including a control unit for controlling the selector modules to select which second connector to connect to the first connector.Type: GrantFiled: December 19, 2017Date of Patent: July 11, 2023Assignee: SAFRAN ELECTRONICS & DEFENSEInventors: Pascal Regache, Philippe Elie
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Patent number: 11698317Abstract: A measurement device for measuring the pressure of a wheel (3) of a vehicle, the measurement device comprising a stationary portion (5) and a movable portion (14) for being driven in rotation by the wheel, the stationary portion including a first printed circuit (7) having at least one first track formed thereon defining a first winding, the movable portion including a second printed circuit (16) having at least one second track formed thereon defining a second winding, the second printed circuit being arranged to be connected to a pressure sensor (15), the first winding and the second winding being coupled together to form a wireless communication channel, the measurement device being arranged in such a manner that the pressure sensor is electrically powered by the stationary portion via the wireless communication channel, and in such a manner that uplink data comprising pressure measurement data is transmitted to the stationary portion (5) by the movable portion (14) via the wireless communication channel.Type: GrantFiled: October 2, 2019Date of Patent: July 11, 2023Assignees: SAFRAN LANDING SYSTEMS, SAFRAN ELECTRONICS & DEFENSEInventors: Joel Zabulon, Didier Levavasseur
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Patent number: 11698003Abstract: A cooling device (11) for a turbine of a turbomachine extending along an axis includes at least one radially inner metal sheet (14) and one radially outer metal sheet (15) that are joined to one another and delimit, between them, cooling air circulation channels (17) extending circumferentially from a connection region (16). Each channel (17) includes at least one air inlet and air ejection orifices (19), that are designed to be oriented toward a region to be cooled. The cooling device also includes at least one cooling duct (21) intended for the circulation of cooling air, the duct (21) located radially outside said metal sheets (14, 15) and close to or in contact with the metal sheets so as to cool said metal sheets using the cooling air circulating in the duct (21), the cooling duct (21) extending axially and arranged toward the circumferential end regions of the channels (17).Type: GrantFiled: October 27, 2017Date of Patent: July 11, 2023Assignee: SAFRAN AIRCRAFT ENGINESInventors: Baptiste Marie Aubin Pierre Jouy, Nicolas Contini, Arnaud Doublier, Vincent Dubois Dorogi, Sébastien Jean Laurent Prestel
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Patent number: 11698004Abstract: An aircraft propulsion assembly includes a turbine engine surrounded by a nacelle with an annular air-intake lip extending around the turbine engine by two annular walls, inner and outer, respectively, intended for being swept across by air flows at least when the aircraft is in flight. The inner and outer walls each includes or supports at least one network of pipes forming heat exchangers. The inner wall pipe network having liquid outlet connected with a liquid intake of the outer wall pipe network. The propulsion assembly further includes means for circulating the liquid, connected to at least one liquid intake of the network of pipes of the inner wall.Type: GrantFiled: April 12, 2018Date of Patent: July 11, 2023Assignees: SAFRAN AIRCRAFT ENGINES, SAFRAN NACELLESInventors: Sébastien Oriol, Mohammed-Lamine Boutaleb, Vincent Jean-François Peyron
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Patent number: 11698029Abstract: A dual-flow turbojet engine having a central shaft surrounded by a high-pressure body which rotate about the same longitudinal axis while being independent in rotation, and including a fan driven by the central pressure shaft; a high-pressure compressor and a high-pressure turbine mounted on the high-pressure body; an inter-turbine casing; a low-pressure turbine mounted on a low-pressure rotor surrounding the central shaft; an exhaust casing on which an output cone is mounted; a reduction gear with which the low-pressure rotor drives the central pressure shaft; two bearings mounted on the exhaust casing and respectively receiving the central shaft and the low-pressure rotor; a bearing mounted on the inter-turbine casing and receiving the low-pressure rotor.Type: GrantFiled: November 21, 2019Date of Patent: July 11, 2023Assignee: SAFRAN AIRCRAFT ENGINESInventors: Alexandre Jean-Marie Tan-Kim, Yanis Benslama, Jérémy Dievart, Julien Fabien Patrick Becoulet
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Publication number: 20230213399Abstract: A hydraulic torque measurement device for an aircraft engine unit includes a hermetically sealed enclosure having a rigid wall and a deformable wall that define an internal volume. The device further includes at least one pressure measuring element capable of measuring the pressure prevailing in the internal volume. The hydraulic torque measuring device allows a service state in which the internal volume is filled exclusively with an incompressible liquid, and in which the deformable wall is configured to be subjected to a pressure force. In some embodiments, the hydraulic torque measurement device is suitable for use with a gearbox.Type: ApplicationFiled: May 9, 2021Publication date: July 6, 2023Applicant: SAFRAN HELICOPTER ENGINESInventor: Laurent Louis Sylvain HOUSSAYE
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Publication number: 20230212982Abstract: 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.Type: ApplicationFiled: May 25, 2021Publication date: July 6, 2023Applicant: SAFRANInventor: Hugo Pierre Mohamed JOUAN
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Publication number: 20230212952Abstract: A turbomachine turbine nozzle extending around a central axis, including at least one radially outer shroud, at least one radially inner shroud, and at least one blade made of ceramic matrix composite material, distinct from the radially inner shroud and from the radially outer shroud, and extending radially between the radially inner shroud and the radially outer shroud, the blade being hollow and including a cavity opening at a radially inner end and at a radially outer end of the blade, the nozzle including at least one tubular mast arranged in the cavity of the blade and allowing routing the ventilation air passing through the cavity of the blade, the mast including a radially outer end attached to the radially outer shroud, and a radially inner end cooperating with a radial flange for positioning the radially inner shroud.Type: ApplicationFiled: April 28, 2021Publication date: July 6, 2023Applicants: SAFRAN AIRCRAFT ENGINES, SAFRAN CERAMICSInventors: Antoine Claude Michel Etienne DANIS, Clément JARROSSAY, Lucien Henri Jacques QUENNEHEN, Nicolas Paul TABLEAU, Matthieu Arnaud GIMAT
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Publication number: 20230212983Abstract: 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: ApplicationFiled: May 27, 2021Publication date: July 6, 2023Applicant: SAFRANInventors: Thierry SIBILLI, Sarah REBHOLZ
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Patent number: 11692459Abstract: A method for manufacturing a turbine engine part in which a first rough casting element includes a first face and a second face opposite to each other is assembled by the second face on an orifice which has a second element of the part. The method includes machining a through-cavity in the first element which opens at the first face and from the second face of the first element and machining the first face of the first element so as to form an area suitable for ensuring the attachment of a conduit on the first element. The machining of the cavity and of the first face is achieved by using a machining reference frame based on the second element.Type: GrantFiled: March 21, 2022Date of Patent: July 4, 2023Assignee: SAFRAN AIRCRAFT ENGINESInventors: Nicolas Pommier, Mathieu Bissardon, Mathieu Delalandre, Stephane Nicolas Piron, Olivier Renon
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Patent number: 11692453Abstract: An aircraft turbine engine includes a gas generator and a fan arranged upstream from the gas generator and configured to generate a main gas flow, one portion of which flows in a flow path of the gas generator to form a primary flow, and another portion of which flows in a flow path around the gas generator to form a secondary flow. The gas generator includes a low-pressure compressor that includes a rotor driving the fan. The turbine engine further includes an electric machine. The electric machine includes a rotor rotated by the rotor of the low-pressure compressor, and a stator extending around the rotor of the electric machine and configured to be cooled by the primary flow.Type: GrantFiled: October 22, 2019Date of Patent: July 4, 2023Assignee: SAFRAN AIRCRAFT ENGINESInventors: Gilles Alain Marie Charier, Caroline Marie Frantz, Loïc Paul Yves Guillotel, Vincent François Georges Millier
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Patent number: 11692480Abstract: An air intake scoop intended to be fastened on a panel of an aircraft includes an air inlet mouth having a wall, a peripheral collar intended to be fastened to the panel, and a bearing element intended to support the air circulation duct. The air inlet mouth is made of a thermoplastic material and the bearing element is fastened on the peripheral collar so as to achieve a pressure barrier in case of breakage of the wall of the air inlet mouth.Type: GrantFiled: August 27, 2019Date of Patent: July 4, 2023Assignee: Safran NacellesInventors: François Bellet, Laurent Georges Valleroy, Mathieu David
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Patent number: 11691611Abstract: The invention provides a method of electrically powering an electromechanical braking actuator (1) fitted to an aircraft wheel brake, in which the power supply current (I) delivered to the electromechanical braking actuator is saturated to a saturation value (Isat) in order to limit the current consumed by the electromechanical braking actuator and thereby limit the forces developed by the actuator. The method includes the step of determining the saturation value (Isat) as a function of an internal temperature (T) of the electromechanical braking actuator while it is in operation.Type: GrantFiled: April 7, 2020Date of Patent: July 4, 2023Assignee: SAFRAN LANDING SYSTEMSInventors: Olivier Frey, Frédéric Pithoud, Serge Barthelemy
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Patent number: 11691737Abstract: A vehicle seat including: a seat back; a seat pan; and one or more side support elements is disclosed. Each side support element is moveable with respect to the seat back between: a stowed configuration, in which the side support element is stowed flush with, or is stowed within or behind the seat back; and a deployed configuration, in which the side support element extends outwardly from the seat back, generally in the same direction that the seat back faces, so as to offer support to the side of a vehicle user sitting in the vehicle seat. A row of two or more such vehicles seats is also disclosed, in which all of the seats of the row face in the same direction, and adjacent seats within the row are connected to each other.Type: GrantFiled: May 19, 2021Date of Patent: July 4, 2023Assignees: UNIVERSAL MOVEMENT LTD, SAFRAN SEATSInventors: Luke Miles, Hugo Benedict Jamson, Cheuk Wah Vincent Fan
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Patent number: 11691716Abstract: A propulsion system for an aircraft, comprising at least one rotor and a nacelle fairing extending around the at least one rotor with respect to an axis of rotation of the rotor, the nacelle fairing comprising: an upstream section forming an inlet section of the nacelle fairing; a downstream section wherein a downstream end forms an outlet section of the nacelle fairing; and an intermediate section connecting the upstream and downstream sections, wherein the downstream section comprises a radially inner wall and a radially outer wall made of a deformable shape memory material, and further comprising at least one actuator mechanism with at least one cylinder configured to cooperate with one or more components, projections, etc., embedded in an inner surface of the radially outer wall so as to vary an outer diameter of the outlet section between a minimum diameter and a maximum diameter.Type: GrantFiled: April 10, 2020Date of Patent: July 4, 2023Assignee: SAFRANInventors: Jean-Louis Robert Guy Besse, Ye-Bonne Karina Maldonado
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Patent number: 11692450Abstract: A labyrinth sealing joint for a turbomachine, for example of an aircraft, includes a rotor element extending about an axis (A), and a stator element extending around the rotor element, the rotor element having two annular lips extending radially outwards and surrounded by at least one abradable element carried by the stator element. A plurality of gas passage cavities are arranged circumferentially next to one another between the two lips which are interconnected by connecting partitions, wherein at least one of the lips has at least one axial gas passage opening that leads into at least some of the cavities, wherein the partitions extend substantially axially between the lips and define sectors of gas passage spaces between them, the sectors of spaces being divided by separation walls for forming the cavities.Type: GrantFiled: June 11, 2019Date of Patent: July 4, 2023Assignee: SAFRAN AIRCRAFT ENGINESInventor: Clément Raphaël Laroche
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Patent number: 11692512Abstract: A fan module for an aircraft turbine engine, this module comprising a fan and an electrical machine, such that the electrical machine is coaxially mounted downstream of the fan and comprises a rotor coupled to rotate with the fan and an annular member with generally C-shaped axial cross-section, the opening of which is axially orientated and receives the rotor, this member comprising a radially outer portion forming a stator, and a radially inner portion forming a support for bearings guiding the rotor.Type: GrantFiled: October 16, 2019Date of Patent: July 4, 2023Assignee: SAFRAN AIRCRAFT ENGINESInventors: Loic Paul Yves Guillotel, Tewfik Boudebiza, Gilles Alain Marie Charier, Caroline Marie Frantz, Vincent Francois Georges Millier
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Patent number: 11694669Abstract: A method for manufacturing a cellular core for an acoustic panel is provided. The cellular core includes at least one plurality of acoustic cells and a plurality of de-icing channels that extend longitudinally, each de-icing channel being transversely interposed between two successive cells, and the de-icing channels being adapted to channel a de-icing fluid. A manufacturing step includes producing the acoustic cells and the de-icing channels as a single piece such that the cellular core manufactured during the manufacturing step forms a monolithic part.Type: GrantFiled: March 6, 2020Date of Patent: July 4, 2023Assignee: Safran NacellesInventors: Quentin Alban Guillaume Benard, Virginie Emmanuelle Anne Marie Digeos
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Patent number: 11691751Abstract: An accumulator designed to damp the pressure waves of the hydraulic shocks originating in a downstream section of a duct is arranged inside the duct, with the opening of the accumulator pointing downstream. This results in excellent absorption of the pressure wave and protection of the circuit from possible accumulations of air, water or ice, there being no areas where the flow stagnates. Immersing the accumulator in the flow also makes it possible to ensure that the equipment is protected in the event of a fire.Type: GrantFiled: December 15, 2017Date of Patent: July 4, 2023Assignee: SAFRAN AIRCRAFT ENGINESInventor: Loic Pora