Patents Assigned to SAFRAN
  • Fan or propeller vane for an aircraft turbomachine and method for manufacturing same
    Patent number: 11933194
    Abstract: 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: Grant
    Filed: December 17, 2020
    Date of Patent: March 19, 2024
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Vivien Mickael Courtier, Teddy Fixy, Clement Pierre Postec, Eddy Keomorakott Souryavongsa
  • Speed reduction gear for an aircraft turbomachine
    Patent number: 11933229
    Abstract: 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: Grant
    Filed: February 6, 2023
    Date of Patent: March 19, 2024
    Assignee: SAFRAN TRANSMISSION SYSTEMS
    Inventors: Patrice Julien Ptaszynski, Antoine Jacques Marie Pennacino, Boris Pierre Marcel Morelli
  • Modularity of an aircraft turbomachine
    Patent number: 11933230
    Abstract: 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: Grant
    Filed: November 2, 2021
    Date of Patent: March 19, 2024
    Assignee: Safran Aircraft Engines
    Inventors: Paul Ghislain Albert Levisse, Olivier Belmonte
  • Fuel metering unit for an aircraft engine
    Patent number: 11933224
    Abstract: 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: Grant
    Filed: November 12, 2019
    Date of Patent: March 19, 2024
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Guilhem Alcide Auguste Foiret, Arnaud Bernard Clément Thomas Joudareff
  • Turbojet engine comprising a nacelle with an air intake to promote a reversed thrust phase
    Patent number: 11933246
    Abstract: 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: Grant
    Filed: April 8, 2020
    Date of Patent: March 19, 2024
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Daniel-Ciprian Mincu, Jean-Loïc Hervé Lecordix, Nicolas Joseph Sirvin, Frédéric Dautreppe, Anthony Binder, Eva Julie Lebeault
  • Abradable coating for rotating blades of a turbomachine
    Patent number: 11933181
    Abstract: 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: Grant
    Filed: May 17, 2022
    Date of Patent: March 19, 2024
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Philippe Charles Alain Le Biez, Nicolas Droz, Lisa Pin, Serge Georges Vladimir Selezneff
  • Method for coating an aircraft turbomachine component
    Patent number: 11931770
    Abstract: 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: Grant
    Filed: April 21, 2020
    Date of Patent: March 19, 2024
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventor: Mathieu Julien Charlas
  • Curvic type coupling for turbomachine with locking
    Patent number: 11933191
    Abstract: A coupling for a turbomachine, including a first and a second disc attached along an axis, and extending in majority respectively from a first and from a second side of a median plane normal to the axis, the first and the second discs being provided respectively with first and second teeth mutually engaging through the median plane to form a curvic connection. Several first teeth each include a first protuberance jutting out towards the axis while extending from the second side; several second teeth each include a second protuberance jutting out towards the axis of rotation while extending from the first side; the first protuberances are spaced apart from the second protuberances along the axis; at least one blocking member is brought to be supported against the first and second protuberances to block axially the first element relatively to the second element.
    Type: Grant
    Filed: August 23, 2019
    Date of Patent: March 19, 2024
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventor: Clement Raphael Laroche
  • Tray table with honeycomb core
    Patent number: 11932403
    Abstract: 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: Grant
    Filed: January 10, 2022
    Date of Patent: March 19, 2024
    Assignee: Safran Seats USA LLC
    Inventors: Gokul Ramarathnam, Reza Mansouri
  • Propulsion system for an aircraft
    Patent number: 11932410
    Abstract: A propulsion system for an aircraft includes a rotor and a nacelle fairing that extends around the rotor in relation to an axis. The nacelle fairing includes an upstream portion forming an inlet section of the nacelle fairing as well as a downstream portion, a downstream end of which forms an outlet section of the nacelle fairing. The downstream portion includes radially inner and outer walls, both of which are made of a deformable shape memory material. The wall has independently actuatable piston actuator mechanisms, each actuator mechanism being actuatable independently of the others and being designed to cooperate with means built into an inner surface of the wall to deform the wall in a radial direction in relation to the axis under the effect of a predetermined displacement command.
    Type: Grant
    Filed: October 12, 2020
    Date of Patent: March 19, 2024
    Assignees: SAFRAN, SAFRAN HELICOPTER ENGINES
    Inventors: Jean-Louis Robert Guy Besse, Ye-Bonne Karina Maldonado
  • SYSTEM FOR CONTROLLING DISCHARGE DOORS OF A TURBOMACHINE
    Publication number: 20240084713
    Abstract: A system for controlling discharge doors of a turbomachine includes: a ring and a device connecting the ring to each discharge door.
    Type: Application
    Filed: January 26, 2022
    Publication date: March 14, 2024
    Applicant: SAFRAN
    Inventors: Nicolas Claude PARMENTIER, Gabriel PEREZ
  • DRIVE ASSEMBLY FOR A MECHANICAL REDUCER FOR AN AIRCRAFT TURBOMACHINE
    Publication number: 20240084712
    Abstract: A drive assembly for a mechanical reducer for a turbomachine, in particular for an aircraft, includes planet gears, a planet carrier having at least one transverse wall, plain bearings for guiding the planet gears in rotation, and an oil supply circuit for the plain bearings. The planet carrier has collars for attaching the planet gears to the at least one transverse wall, and each of the planet gears includes at least one external cylindrical surface for forming an oil film with an internal cylindrical surface portion of each of the collars for forming said oil film.
    Type: Application
    Filed: September 12, 2023
    Publication date: March 14, 2024
    Applicant: SAFRAN TRANSMISSION SYSTEMS
    Inventors: Bálint PAP, Clément JARROUX, Guillaume Pierre MOULY, Pierre-Damien TUNE
  • PLAIN BEARING FOR AN AIRCRAFT TURBOMACHINE MECHANICAL REDUCER
    Publication number: 20240084711
    Abstract: A plain bearing for a mechanical reducer for a turbomachine is integrally formed and includes a cylindrical body. The cylindrical body has an external cylindrical guide surface, a first axial mounting extension, a first circumferential edge extending around the first extension, a second axial mounting extension, and a second circumferential edge extending around the second extension. The plain bearing further includes an attachment cover connected to the first axial extension and extending axially opposite said first edge.
    Type: Application
    Filed: September 8, 2023
    Publication date: March 14, 2024
    Applicant: SAFRAN TRANSMISSION SYSTEMS
    Inventors: Bálint PAP, Cyrille CASTELOOT
  • PLANET CARRIER FOR A SPEED REDUCER ON AN AIRCRAFT TURBOMACHINE
    Publication number: 20240084876
    Abstract: A planet carrier for a speed reducer of an aircraft turbomachine, the planet carrier including a cage carrier and a cage. The cage can have two parts: a first part having a wall and bridges, these bridges projecting axially from a face of this wall and including first axial ends connected to this face and second free axial ends; and a second part having another of the walls, this other wall including a face to which the free ends of the bridges are applied. The two parts of the cage can be attached together by screws.
    Type: Application
    Filed: September 6, 2023
    Publication date: March 14, 2024
    Applicant: SAFRAN TRANSMISSION SYSTEMS
    Inventors: Guillaume Pierre MOULY, Guillaume Julien BECK, Patrice Julien PTASZYNSKI, Jean-Pierre SEREY, Adrien Louis SIMON
  • ELECTRICAL DISTRIBUTION SPACECRAFT, AND ASSOCIATED METHOD
    Publication number: 20240083599
    Abstract: A spacecraft for the distribution of electrical energy to client craft at points situated in free space, in orbit and/or on a celestial body includes a main structure equipped with an electric thruster, with a chemical thruster and with a solar generator, a first fuel container for fuel intended for the electric thruster, and a second fuel container for fuel intended for the chemical thruster. The spacecraft is able to be modulated such that the main structure can be coupled/decoupled alternatively to/from the first container or the second container, the first container and the second container are able to be coupled/decoupled to/from one another, and the solar generator can be deployed or retracted.
    Type: Application
    Filed: November 13, 2023
    Publication date: March 14, 2024
    Applicants: Centre National d'Études Spatiales, Safran Spacecraft Propulsion, THALES
    Inventors: Pascal BULTEL, Gautier DURAND, Nicolas THIRY, Marie ANSART, Gilles BOUHOURS, Olivier DUCHEMIN, Frédéric MARCHANDISE
  • Electric machine with more precise measurement
    Patent number: 11929650
    Abstract: The invention relates to an electric machine comprising a rotor and a stator. The rotor (40, 4) comprises a plurality of permanent magnets (4), the stator comprises a plurality of coils suitable for being powered by an electric current and two Hall effect sensors (6) on supports (60). The sensors are configured to detect a change in gradient of the normal component of a magnetic field generated by the permanent magnets (4). The stator comprises a part (7) comprising —a first zone (7a), —a second zone (7b), and a third zone (7c) extending from the first zone (7a) up to the second zone (7b). The maximum radial thickness of the third zone (7c) is less than the minimum radial thickness of the first zone and the second zone.
    Type: Grant
    Filed: October 23, 2019
    Date of Patent: March 12, 2024
    Assignee: SAFRAN ELECTRONICS & DEFENSE
    Inventors: Alberto Rossi, Jérôme Piaton, Benjamin Daguse
  • Method for manufacturing a blade comprising a bathtub tip integrating a small wall
    Patent number: 11925986
    Abstract: The invention relates to a method for manufacturing a turbine engine blade (16) including an active-surface wall (17) and a passive-surface wall (18) separated from one another, this blade (16) including a tip that has a closing wall grouping together the active-surface (17) and passive-surface (18) walls in the region of this tip to define the bottom (23) of a bathtub tip shape located at the tip of the blade, the method comprising a moulding step implementing a core defining the bathtub tip shape. According to the invention, there is a step of adding metal to the bottom (23) of the bathtub tip by means of a Direct Laser Additive Manufacturing (CLAD) method, to deposit material onto the bottom of the bathtub tip to form therein an inner partition (28) supported by the bottom thereof (23).
    Type: Grant
    Filed: June 27, 2016
    Date of Patent: March 12, 2024
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Matthieu Jean Luc Vollebregt, Coralie Guerard, Patrick Emilien Paul Emile Huchin
  • Lubrication device for turbomachine reduction gear
    Patent number: 11927262
    Abstract: Lubrication device for a turbomachine reduction gear, the device comprising an annular lubricating oil collecting cup delimited by a first wall and a second wall, said cup being divided by internal walls extending between the first wall and the second wall so as to define a plurality of angular sectors forming oil collection basins, the basins being circumferentially adjacent around the axis and comprising lubricating oil outlets, characterized in that one or more of said internal walls have openings allowing oil to pass between the circumferentially adjacent basins, characterized in that said openings (58) are formed in one or more of said internal walls so as to define one or more rows of openings in said one or more internal walls.
    Type: Grant
    Filed: May 3, 2022
    Date of Patent: March 12, 2024
    Assignee: SAFRAN TRANSMISSION SYSTEMS
    Inventors: Bálint Pap, Patrice Jocelyn Francis Gedin, Antoine Jacques Marie Pennacino
  • Tool and method for disassembling and moving a TRV-type turbine casing of an aircraft turbine engine
    Patent number: 11927107
    Abstract: A TRV-type turbine casing includes inner and outer annular shrouds that extend one inside the other and about the same axis and are connected together by arms. A tool for disassembling and moving the casing has a lower carriage for moving the tool, and an upper plate to be attached to the turbine casing. The plate is supported by the carriage and includes first members that cooperate with a first annular flange of one of the shrouds to support the casing and axially immobilize the casing relative to the tool. The plate further includes second members that cooperate with a second annular flange of the other shroud in order to prevent and/or guide the rotation of the casing about the axis.
    Type: Grant
    Filed: July 16, 2020
    Date of Patent: March 12, 2024
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Sébastien Georges Cistac, Olivier Jean Caudron
  • Acoustic attenuation on a turbine engine wall
    Patent number: 11927133
    Abstract: An acoustic attenuation liner includes a porous coating with a mesh structure, an acoustically absorbent material covered with the porous coating and having a first volume, and at least one cavity created between the acoustically absorbent material and the porous coating and which has a second volume, such as Vcav>3%, wherein the mesh structure has wires separating between them openings passing through the structure, some of which have, when flat, a minimum elementary surface area.
    Type: Grant
    Filed: October 12, 2018
    Date of Patent: March 12, 2024
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Josselin David Florian Regnard, Norman Bruno André Jodet