Patents Assigned to SAFRAN
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Patent number: 11783473Abstract: 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.Type: GrantFiled: August 3, 2021Date of Patent: October 10, 2023Assignees: SAFRAN AIRCRAFT ENGINES, SAFRAN, CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQU, ECOLE NORMALE SUPERIEURE PARIS-SACLAYEInventors: Julien Paul Schneider-Die-Gross, Intisar Belhaj Saad, Arturo Mendoza Quispe, Estelle Marie Laure Parra, Stéphane Roux
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Automated device for inserting sealing pads into one of the sectors of a turbine stator of a turbine
Patent number: 11781438Abstract: A device is suitable for inserting sealing pads into one of the sectors of a turbine stator of a turbine, wherein the turbine stator includes a plurality of sectors with adjacent side faces abutting each other and slots arranged opposite each other in the adjacent side faces of two successive sectors. Each stator is configured to receive a predefined sealing pad. The device includes a support for supporting the sector; a robot arm configured to grip the sealing pads, each predefined in accordance with the slot intended to receive it. The robot arm is configured to insert each predefined sealing pad into the slot intended to receive it of one of the side faces of the sector.Type: GrantFiled: November 4, 2021Date of Patent: October 10, 2023Assignee: SAFRAN AIRCRAFT ENGINESInventors: Enguerrand Frédéric De Agostini, Carlos Alves De Matos, Florian Chauvel, Baptiste Eparvier, Mathias Gagliardo, Abner Wysidi -
Patent number: 11780585Abstract: The present invention relates to an aircraft cabin having a longitudinal axis and comprising at least one aisle and an arrangement of seat units, a seat unit comprising, in particular, a seat provided with a base and a backrest as well as a foot area, the seat being movable between a sitting position and a lying position, the arrangement of seat units comprising: at least one rear group of two seat units, at least one front group of two seat units, each group of two seat units comprising a seat unit arranged on the side of the aisle and referred to as the “aisle-side seat unit” and a seat unit arranged on the side of a window and referred to as the “window-side seat unit”, each seat of a group of seat units having an axis forming a non-zero angle relative to the longitudinal axis of the aircraft cabin, such that the seats of each group are facing the aisle, a first passage for accessing the aisle associated with the window-side seat unit of the rear group extending between the foot area and the seat of theType: GrantFiled: December 9, 2020Date of Patent: October 10, 2023Assignees: Safran Seats, Safran Seats USA LLCInventors: Florelle Rousse, Arthur Glain, Adrien Beauvais, Nguyen Foek Le, David Morales
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Publication number: 20230318416Abstract: 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.Type: ApplicationFiled: August 13, 2021Publication date: October 5, 2023Applicants: SAFRAN HELICOPTER ENGINES, SAFRANInventors: Camel SERGHINE, Thomas KLONOWSKI, Pierre Gabriel Marie QUINIO, Sabrina Siham AYAT, Eric ROULAND, Sébastien YON, Albert MUTABAZI
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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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Publication number: 20230313695Abstract: A nozzle for a turbomachine turbine. The nozzle includes blades made of ceramic matrix composite material, and at least one metal liner passing through a respective blade. The liner is connected in a sealed manner to a metal internal shroud so as to guide a ventilation fluid through the blade. The nozzle can be configured to maintain effective sealing in spite of the different thermal expansions of the blade and of the internal shroud.Type: ApplicationFiled: October 1, 2020Publication date: October 5, 2023Applicants: SAFRAN AIRCRAFT ENGINES, SAFRAN CERAMICSInventors: Clément JARROSSAY, Sébastien Serge Francis CONGRATEL, Aurélien GAILLARD, David René Pierre LE CAIR, Matthieu Arnaud GIMAT
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Publication number: 20230311428Abstract: A method for manufacturing a part made of composite material for a turbomachine, in particular of an aircraft, includes the steps of: b) arranging a preform made of fibers in a mold, c) injecting polymerizable resin into the mold, d) machining the part, and e) visually checking the part. Step b) is preceded by a step a) in which at least one compliance coating is deposited in the mold. The compliance coating has a calibrated thickness (X) and at least one visual aspect identifiable by an operator. The coating is configured to cover at least one area of the preform and to be rigidly attached thereto by the resin at the end of step c) Step e) includes verifying, by the operator, the presence of the aspect in the area.Type: ApplicationFiled: June 10, 2021Publication date: October 5, 2023Applicant: SAFRAN AIRCRAFT ENGINESInventors: Matthieu Patrick Jean Roger PERLIN, Arthur BOUCHAUD, Romain PLANTE
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Patent number: 11773747Abstract: A turbine rotor for aircraft turbine engine includes a mobile disc supporting mobile blades, the mobile disc including a plurality of slots into which are inserted the roots of the mobile blades a passage being formed between the bottom of the slots and the roots of the mobile blades inserted into the slots. The rotor also includes a circulation channel configured to allow circulation of fluid, the circulation channel including the passage, and a calibration device configured to allow the flow of a first fluid flow rate in the circulation channel when the temperature within the channel is less than a predetermined temperature threshold value, and to change state so as to allow the flow of a second fluid flow rate, greater than the first flow rate, in the channel, when the temperature within the channel is greater than or equal to said predetermined threshold value.Type: GrantFiled: January 15, 2021Date of Patent: October 3, 2023Assignee: SAFRAN AIRCRAFT ENGINESInventors: Eddy Stephane Joel Fontanel, Matthieu Etienne Attali, Gerard Philippe Gauthier, Wilfried Lionel Schweblen
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Patent number: 11772778Abstract: The invention describes a system for controlling the cyclic setting of blades (1) of a turbine engine propeller, the blades (1) being arranged in a plane normal to the axis of rotation (r) of the propeller, the system comprising: —a plate assembly (40) that can be tilted relative to the normal plane (P), —an articulation system (50) articulating the plate assembly (40) relative to the blades (1) such that tilting the plate assembly (40) modifies the setting of the blades (1), —a force sensor (5) designed to measure a force applied in the normal plane (P) by an air flow at the inlet of the propeller blades (1), —a cylinder (60) suitable for tilting the plate assembly (40) in response to a force measured by the force sensor (5).Type: GrantFiled: October 2, 2020Date of Patent: October 3, 2023Assignee: SAFRAN AIRCRAFT ENGINESInventors: Tewfik Boudebiza, Julien Michel Patrick Christian Austruy, Gilles Alain Marie Charier, Cedrik Djelassi
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Patent number: 11773788Abstract: The present disclosure concerns the communication between electronic systems in an aircraft subassembly such as a propulsion unit. This communication is at least partially carried out by light signals transmitted through at least one interior volume of the sub-assembly, this interior volume defining an optical channel. To this end, at least one of these systems includes an emitter arranged to emit a light signal and modulate it depending on data to be transmitted generated by this system, and at least one other of these systems includes at least one receiver capable of receiving this light signal.Type: GrantFiled: December 18, 2020Date of Patent: October 3, 2023Assignee: Safran NacellesInventors: Patrick Gonidec, Jean-Paul Rami
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Patent number: 11772810Abstract: An aircraft includes a fuselage disposed in a longitudinal plane and two propulsion units disposed in a plane transverse to the longitudinal plane, on either side of the fuselage. A nacelle for use in the aircraft includes a proximal upper dial, a distal upper dial, a proximal lower dial, a distal lower dial, an upstream section, a middle section, a downstream section having a trailing edge, and at least one surface heat exchanger, called a cold source exchanger, between a heat transfer fluid and a cold air flow, integrated into a closed circuit in which the heat transfer fluid circulates, and disposed in any one of the proximal upper, distal upper and/or distal lower dials, and in the middle and/or downstream section(s).Type: GrantFiled: April 3, 2020Date of Patent: October 3, 2023Assignee: Safran NacellesInventors: Vincent Peyron, Jean-Nicolas Bouchout
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Patent number: 11773727Abstract: A blade of a turbomachine turbine, including a platform and a vane, including a cooling area extending along the trailing edge, with three distinct types of orifices, wherein the blade includes, at the root of the blade, a first type of orifices formed in the thickness of the trailing edge fillet, at the top of the blade, a third type of orifice formed in the thickness of at least one of the lower surface and upper surface walls, and in the middle of the blade, a second type of orifice formed in the thickness of at least one of the lower surface and upper surface walls. The lower surface wall, the upper surface wall and the trailing edge fillet define a dihedral with a radially changing radius and spacing.Type: GrantFiled: March 9, 2021Date of Patent: October 3, 2023Assignee: SAFRAN AIRCRAFT ENGINESInventors: Leandre Ostino, Filippo Pagnoni
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Patent number: 11772359Abstract: A method for manufacturing a turbine nozzle vane made of ceramic matrix composite material, wherein the vane is manufactured using a first fibrous preform including a hollow central section intended to form a fibrous reinforcement of an airfoil of the vane to be obtained, and a pair of second fibrous preforms each having an opening with a shape of the airfoil of the vane to be obtained.Type: GrantFiled: June 23, 2021Date of Patent: October 3, 2023Assignee: SAFRAN CERAMICSInventors: Matthieu Arnaud Gimat, Julien André Roger Mateo, Clément Marie Benoît Roussille
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Patent number: 11772777Abstract: A variable pitch bladed disc including a plurality of blades, each being of variable pitch about a blade axis of rotation and having a root, the plurality of blades including at least one first blade and at least one second blade, a plurality of rotor connecting shafts, each shaft having a root and a tip, the root of each blade being mounted on the tip of a corresponding rotor connecting shaft via a pivot so as to allow each blade to be rotated about the blade axis of rotation, the first blade having a first rotation axis inclination such that the rotation axis thereof is inclined in a fixed manner with respect to a radial axis passing through the root of the corresponding shaft, and the second blade has a second rotation axis inclination different from the first rotation axis inclination.Type: GrantFiled: June 7, 2021Date of Patent: October 3, 2023Assignee: SAFRAN AIRCRAFT ENGINESInventors: Clement Marcel Maurice Dejeu, Jonathan Evert Vlastuin, Mathieu Simon Paul Gruber
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Patent number: 11773779Abstract: An air inlet into a nacelle of an aircraft turbojet engine having a de-icing device and extends along an axis X, an air stream flowing in the air inlet from upstream to downstream, the inlet comprising an inner wall and an outer wall which are connected by a leading edge, the inner wall having a plurality of air delivery lines, each air delivery line having a plurality of through-holes designed to blow elementary streams from the hot air source in order to de-ice said inner wall, the air delivery lines being parallel to one another in a cylindrical projection plane, each air delivery line having a depth P3 defined along the axis X as well as a length L3 defined along the axis Y in the cylindrical projection plane, two adjacent air delivery lines being spaced apart by a distance D3, each position along the axis Y with no more than one through-hole, the ratio of the distances L3/D3 being between 0.8 and 1.Type: GrantFiled: November 20, 2020Date of Patent: October 3, 2023Assignee: SAFRAN NACELLESInventor: Hervé Léopold Hurlin
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Patent number: 11777370Abstract: An aeronautical turbogenerator for hybrid electric propulsion includes a heat engine and an electrical generator coupled mechanically to the heat engine and including a rotor and a stator, the rotor extending in an axial direction and including a common magnetized rotor yoke comprising a plurality of permanent magnets defining at least three axially distributed movable annular rings, the stator including a magnetic stator yoke comprising a plurality of electrical windings defining axially and/or circumferentially distributed stationary sectors, at least two stationary sectors, one of which covers axially at least two movable annular rings, being arranged angularly so as not to mutually coincide and thus deliver at least two distinct and independent voltage levels.Type: GrantFiled: July 24, 2020Date of Patent: October 3, 2023Assignees: SAFRAN HELICOPTER ENGINES, SAFRANInventors: Loïs Pierre Denis Vive, Christophe Ludovic Jean-Claude Viguier
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Patent number: 11772155Abstract: A method for manufacturing a metal workpiece by casting a metal alloy in a mould, in which prior to the casting, a chart is determined providing a risk of appearance of recrystallised grains during the casting and/or solidification of the metal workpiece, depending on temperature and plastic deformation energy conditions undergone by the metal workpiece, the casting of the metal alloy in the mould being implemented under casting and solidification conditions determined using the chart in order for the temperature and plastic deformation energy conditions undergone by the metal workpiece to be less than a given threshold for the risk of appearance of recrystallised grains.Type: GrantFiled: September 4, 2020Date of Patent: October 3, 2023Assignee: SAFRAN AIRCRAFT ENGINESInventors: Nicolas Romain Benjamin Leriche, Serge Alain Fargeas, Fabien Corpace
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Patent number: 11773733Abstract: A fibrous texture forming the fibrous reinforcement of a turbomachine blade made of composite material which has a three-dimensional weaving between warp yarns or strands made of first fibers and weft yarns or strands made of first fibers, the texture including a blade root portion, a blade airfoil portion and a free end, the texture extending along the transverse direction between a first edge corresponding to a leading edge of the blade and a second edge corresponding to a trailing edge of the blade. The blade airfoil portion has a reinforced area extending along the longitudinal direction from the free end over a first length, and along the transverse direction from the second edge over a second length less, the reinforced area including weft yarns or strands made of second fibers different from the first fibers, the second fibers having an elongation at break greater than the first fibers.Type: GrantFiled: March 18, 2021Date of Patent: October 3, 2023Assignee: SAFRAN AIRCRAFT ENGINESInventors: Gilles Pierre-Marie Notarianni, Teddy Fixy, Paula Salas De Los Rios
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Patent number: 11773740Abstract: Platform for an aircraft turbo machine fan rotor, the platform being configured to be secured to a fan disc between two adjacent fan blades. The platform further including a longitudinal wall defining an aerodynamic external face. The wall includes a honeycomb structure interposed between two skins which are respectively an internal skin and an external skin, with the external skin defining the aerodynamic external face.Type: GrantFiled: April 23, 2021Date of Patent: October 3, 2023Assignee: SAFRAN AIRCRAFT ENGINESInventors: Thierry Francois Maurice Duchatelle, Yann Andre Maurice Perrin
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Patent number: 11772779Abstract: Propulsion assembly for an aircraft, comprising a fuselage extending along a longitudinal axis and enclosing an inner enclosure, at least one ducted engine fixed to the fuselage and comprising an air inlet section, the air inlet section being disposed at least partly in the inner enclosure, at least one plenum chamber disposed in the inner enclosure upstream of the air inlet section and in fluid communication with said air inlet section, at least one air intake formed on an outer wall of the fuselage, the inlet of the air intake being partly delimited by said outer wall of the fuselage, the air intake being configured to ingest external air and deflect it towards the plenum chamber.Type: GrantFiled: July 6, 2020Date of Patent: October 3, 2023Assignee: SAFRAN AIRCRAFT ENGINESInventors: Philippe Gérard Chanez, Jean-Michel Daniel Paul Boiteux, Nicolas Jérôme Jean Tantot