Patents Assigned to SAFRAN
  • Platform first class
    Patent number: 11787545
    Abstract: Described are examples of a seating arrangement for an aircraft with a first seat in a first accommodation space and a second seat in a second accommodation space, wherein the first and second accommodation spaces are configured to share a common floor space at a floor level of the aircraft. One seating arrangement includes a divider screen located between the first and second accommodation spaces, moveable, by sliding in a direction along the common floor space, between a stowed position permitting passenger egress between the first and second accommodation spaces across the common floor space, and a deployed position preventing passenger egress between the first and second accommodation spaces across the common floor space.
    Type: Grant
    Filed: October 4, 2021
    Date of Patent: October 17, 2023
    Assignee: Safran Seats GB Limited
    Inventors: Victor Carlioz, James B. Woodington, Rachel West, Jan Jurre Miedema
  • Fan casing for an aircraft turbomachine directly incorporating abradable portions and having acoustic properties
    Patent number: 11788558
    Abstract: A fan casing for an aircraft turbomachine, the casing including a one-piece annular body, the one piece annular body including a radially internal annular surface, a first annular portion of which is made of an abradable material, wherein a second annular portion of the internal surface comprises blind holes conferring acoustic properties to the second portion.
    Type: Grant
    Filed: August 28, 2019
    Date of Patent: October 17, 2023
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Florent Louis Andre Rognin, Clement Bourolleau, Serge Domingues, Vincent Pascal Fiore, Anwer Siraj
  • Modular exoskeleton structure that provides force assistance to the user
    Patent number: 11787040
    Abstract: A modular exoskeleton structure provides force assistance to a user. The structure includes a base module including a lumbar belt capable of surrounding the waist of the user, a battery and a control unit attached to the lumber belt, a first attachment part attached to the belt and capable of cooperating with a second complementary attachment part of a hip module to attach the hip module to the base module by snapping the second attachment part into the first attachment part, and a third attachment part attached to the belt and capable of cooperating with a complementary fourth attachment part of a back module for attaching the back module to the base module.
    Type: Grant
    Filed: October 15, 2020
    Date of Patent: October 17, 2023
    Assignees: SAFRAN ELECTRONICS & DEFENSE, B-TEMIA INC.
    Inventors: Jordane Grenier, Stephane Bedard, Roland Thieffry, Alexandre Vaure, Jonathan Baptista
  • Thrust reverser cascade including acoustic treatment
    Patent number: 11788489
    Abstract: A cascade for a thrust reversal device intended to be mounted on a turbomachine of an aircraft, the cascade including first partitions extending in a first direction, second fixed partitions extending in a second direction orthogonal to the first direction, and a frame inside which the first and second partitions extend, the frame including at least two fixed walls extending according to the first direction, and at least one part of each first partition extending between two second partitions. At least one first partition is mobile according to the second direction between a first position wherein the first partition is distant, in the second direction, from the fixed walls to form a plurality of resonating cavities with the first partitions and/or the fixed walls, and a second position wherein the one first partition is in contact with a fixed wall or another first partition.
    Type: Grant
    Filed: April 3, 2020
    Date of Patent: October 17, 2023
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Norman Bruno André Jodet, Jéremy Paul Francisco Gonzalez
  • Method of repairing a composite blade
    Patent number: 11787135
    Abstract: The invention relates to a method of repairing a blade (1) made of composite material, extending in a so-called axial direction (X), the said blade (1) comprising a root (2) and a blade (3), the axial end of which opposite the root (2) comprises an area to be repaired, the said blade (3) comprising an intrados (4) surface and an extrados (5) surface.
    Type: Grant
    Filed: April 22, 2020
    Date of Patent: October 17, 2023
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Marc-Emmanuel Jean François Techer, Vincent Bernard Serge Most
  • Method for producing a casing for an aircraft turbine engine
    Patent number: 11788434
    Abstract: Method for manufacturing a casing of an aircraft turbomachine, the casing including an annular shell extending about an axis A and made of a composite material including fibres that are woven and immersed in a resin, the annular layer including an abradable material arranged inside the shell, and covering a first inner annular surface of an intermediate section of the shell, the method including a step of gluing the layer on the first surface, during which the casing is heated and compressed by a system that is present at least partially inside the casing, wherein, prior to the heating and compression of the casing, a forming tool is mounted inside the casing and is made of two rings.
    Type: Grant
    Filed: July 10, 2020
    Date of Patent: October 17, 2023
    Assignees: SAFRAN AIRCRAFT ENGINES, SAFRAN AEROSPACE COMPOSITES
    Inventors: Vincent Pascal Fiore, Gatien Frisoni, Foster Alexander Maxwell, Steven Meserve, Jeffrey Steven Sherman
  • Turbine rotor wheel for an aircraft turbomachine
    Patent number: 11788423
    Abstract: A turbine rotor wheel for an aircraft turbomachine includes a rotor disk, an annular shroud extending around the disk, and blades arranged between the disk and the shroud. The root of each of the blades has two tabs configured for attachment to the disk. The tabs are arranged upstream and downstream, respectively, of a wall of the disk, relative to the axis. The tab arranged upstream is engaged in a first recess of the disk and configured to cooperate by abutment with a peripheral edge of the first recess. The tab arranged downstream is engaged in a second recess of the disk and is configured to cooperate by abutment with a peripheral edge of the second recess.
    Type: Grant
    Filed: December 3, 2020
    Date of Patent: October 17, 2023
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Paul Ghislain Albert Levisse, Olivier Belmonte
  • Counter-rotating turbine of an aircraft turbomachine and method for the non-destructive testing of a counter-rotating turbine rotor
    Patent number: 11788430
    Abstract: A counter-rotating turbine of an aircraft turbomachine, includes a casing including an endoscopy port configured for an endoscopy plug of a non-destructive testing device to pass into the casing. The endoscopy plug includes a mechanism for acquiring and transmitting images. The non-destructive testing device includes a mechanism for receiving and displaying images connected to the mechanism for acquiring and transmitting images by a wireless connection. First and second rotors are configured to rotate in opposite rotation directions, the second rotor having an endoscopy port in which the endoscopy plug is removably attached.
    Type: Grant
    Filed: March 16, 2020
    Date of Patent: October 17, 2023
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Patrick Jean Laurent Sultana, Renaud James Martet, Maxime Aurelien Rotenberg
  • Exhaust casing of a turbomachine with improved aerodynamics
    Patent number: 11788436
    Abstract: A turbomachine exhaust casing extending about an axis including a hub extending about the axis; an external ferrule; arms which extend between the hub and the external ferrule, attachment yokes radially projecting toward the outside of the external ferrule; pockets hollowed into the external ferrule and wherein the yokes are arranged, the pockets extending in a hollow radially projecting toward the inside of the external ferrule; a ring portion which extends radially under the pockets and forms a duct wall by delimiting with the hub a portion of a gas flow duct.
    Type: Grant
    Filed: April 15, 2020
    Date of Patent: October 17, 2023
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Sylvain Yves Jean Duval, Arnaud Lasantha Genilier, Fabien Stephane Garnier, Ludovic Pintat
  • Sealing ring for a wheel of a turbomachine turbine
    Patent number: 11788424
    Abstract: Sealing ring for a wheel of an aircraft turbomachine turbine, the ring having an annular body extending around an axis of revolution and including an outer surface and an inner surface which is coated with an annular layer of an abradable material, the ring further including an annular wall extending around the annular body and at a radial distance from the body, the annular wall including openings through which cooling air flows by impact on the outer surface, wherein the body and the wall are integrally formed.
    Type: Grant
    Filed: May 20, 2020
    Date of Patent: October 17, 2023
    Assignee: SAFRAN HELICOPTER ENGINES
    Inventors: Thomas Louis Guedot, Fabien Hourquet, Eloi Duflos, Patrice Postel
  • Method for monitoring the torsion of a rotary shaft on a turbomachine of an aircraft
    Patent number: 11788931
    Abstract: A method for monitoring the torsion of a rotary shaft on an aircraft turbomachine based on the measurements from at least three sensors distributed along the rotary shaft to divide the shaft into at least two shaft segments, the method comprising: a step of measuring, for each sensor, a parameter dependent on the rotation of the shaft, a step of calculating, for each achievable pair of sensors, a parameter related to the torsion of the shaft, a step of comparing the different calculated parameters related to the torsion of the shaft with references, a step of detecting damage on a shaft segment at the end of the comparison step, and a step of indicating the localization of the damage on the shaft from the shaft segment for which damage has been detected.
    Type: Grant
    Filed: November 13, 2020
    Date of Patent: October 17, 2023
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Alméric Pierre Louis Garnier, Marion Cuny, Tony Alain Roger Joël Lhommeau, Claire Marie Figeureu
  • Injector nose for turbomachine comprising a primary fuel circuit arranged around a secondary fuel circuit
    Patent number: 11788727
    Abstract: An injector nose for a turbomachine includes a primary fuel circuit ending in a fuel-ejection nozzle, and a secondary fuel circuit including an annular-shaped terminal fuel-ejection part arranged around the fuel-ejection nozzle. An upstream part of the primary fuel circuit includes an annular channel, which extends around the secondary fuel circuit and is defined by an external wall of the injector nose. The injector nose includes air intake channels extending through the annular channel and having inlets opening into the external wall and outlets opening into an annular air injection channel arranged radially to the inside in relation to the terminal fuel-ejection part, around the fuel-ejection nozzle, and cooperating with the terminal fuel-ejection part in order to form an aerodynamic secondary injector.
    Type: Grant
    Filed: December 26, 2019
    Date of Patent: October 17, 2023
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Christophe Chabaille, Clément Yves Emile Bernard, Sébastien Christophe Loval
  • Cart for Assembling and Transporting an Aircraft Engine to a Test Cell
    Publication number: 20230322411
    Abstract: Disclosed is a cart (2) for transporting an aircraft engine, comprising a base frame (4) equipped with wheels (6) for riding on a floor; at least two engine arms (14, 16) extending horizontally and movable vertically relative to the base frame, structured and designed for supporting the aircraft engine; and at least two adapter arms (20) extending horizontally at a higher level than the at least two engine arms, structured and designed for supporting an adapter coupled at the top of the aircraft engine. Disclosed is also a method of transporting an aircraft engine to a test cell.
    Type: Application
    Filed: August 19, 2020
    Publication date: October 12, 2023
    Applicant: SAFRAN AERO BOOSTERS
    Inventor: Franck Dumont
  • FREE TURBINE TURBOGENERATOR COMPRISING A REVERSIBLE ELECTRICAL MACHINE COUPLED TO THE FREE TURBINE
    Publication number: 20230323787
    Abstract: Disclosed is a turbogenerator, in particular for an electrically-driven rotary wing aircraft, comprising a gas generator equipped with a first shaft, at least one reversible electrical machine, and a free turbine provided with a second shaft and caused to rotate by a gas flow generated by the gas generator. The second shaft is coupled to the at least one electrical machine during all phases of operation of the turbomachine, and the turbomachine further comprises a single mechanical coupling means for coupling the first mechanical shaft to the second mechanical shaft when the electrical machine is operating in motor mode and mechanically uncoupling the first mechanical shaft from the second mechanical shaft when the electrical machine is operating in generator mode.
    Type: Application
    Filed: October 25, 2021
    Publication date: October 12, 2023
    Applicant: SAFRAN HELICOPTER ENGINES
    Inventors: Loïs Pierre Denis VIVE, Thomas DROUIN, Olivier BEDRINE
  • TURBOMACHINE HAVING A FREE TURBINE COMPRISING ELECTRIC MACHINES ASSISTING A GAS GENERATOR AND A FREE TURBINE
    Publication number: 20230323788
    Abstract: 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: Application
    Filed: November 12, 2021
    Publication date: October 12, 2023
    Applicant: SAFRAN HELICOPTER ENGINES
    Inventors: Loïs Pierre Denis VIVE, Olivier BEDRINE, Thomas DROUIN
  • Turbine having an internal secondary space equipped with fins for correcting gyration of an airflow
    Patent number: 11781442
    Abstract: A turbine includes a rotor surrounded by a stator, a first movable stage including a series of rotating vanes, a second movable stage including a second series of rotating vanes, a distributor including a series of stationary vanes, the vanes including platforms jointly delimiting a separation between a main space in which a hot flow circulates through the vanes, and a secondary space surrounding a hub of the rotor. The rotor includes an aperture through which air is blown towards the secondary space, this air being discharged towards the main space. Straightening fins are carried by the distributor in the secondary space for straightening the air flow in order to change its gyration.
    Type: Grant
    Filed: February 15, 2021
    Date of Patent: October 10, 2023
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventor: Julian Nicolas Girardeau
  • Method for controlling an aircraft taxi system
    Patent number: 11780569
    Abstract: The invention relates to a method for controlling an aircraft taxi system, comprising the steps of: generating a traction command (Com) to control an electric motor of a wheel drive actuator; detecting whether or not an external brake command, intended to control braking of the wheel via the brake, is generated; if an external braking command is generated, producing a predetermined minimum command (Cmp) to control the electric motor so that the drive actuator applies a strictly positive predetermined minimum motor torque to the wheel during braking; detecting whether a speed of the aircraft becomes zero and, if so, inhibiting the predetermined minimum command (Cmp) so that the drive actuator applies zero torque to the wheel.
    Type: Grant
    Filed: February 11, 2021
    Date of Patent: October 10, 2023
    Assignee: SAFRAN LANDING SYSTEMS
    Inventors: Pierre-Yves Liegeois, Laurent Boissard, Djemouai Hadjidj
  • Turbomachine module for a propeller having variable-pitch blades and turbomachine comprising same
    Patent number: 11780562
    Abstract: The invention relates to a turbomachine module (1), comprising: —a rotating housing (7-8) supporting a propeller provided with a plurality of blades (5), —a system for varying the pitch of the propeller blades (5), the system comprising a control means, and a mechanism for varying the pitch of the propeller blades, characterised in that the system is supported by the rotary housing (7-8), in that the control means comprise an annular row of rotary actuators (16), and in that the mechanism for varying the pitch of the blades comprises a synchronisation ring (11) that is driven to rotate by rotary output shafts (17) of the actuators (16), the synchronisation ring (11) being guided in rotation relative to the rotary housing (7-8) by guide means and meshed by a first toothing (13) with pinions (14) of the blades (5).
    Type: Grant
    Filed: July 13, 2020
    Date of Patent: October 10, 2023
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Clement Cottet, Thierry Georges Paul Papin, Regis Eugene Henri Servant
  • Transonic turbomachine compressor
    Patent number: 11781562
    Abstract: A transonic compressor of a turbomachine comprising exactly two or exactly three annular rows of rotor blades and respectively exactly one or exactly two annular rows of intermediate stator vanes interposed between two respective rows of rotor blades, wherein the flow velocity relative to the rotor downstream of the intermediate stator vanes is less than or equal to a Mach number of 0.9 over a radial portion of the blades extending over the radially inner 40% of the blades, and less than or equal to a Mach number of 1 over a radial portion extending over the radially inner 80% of the blades, and less than or equal to a Mach number of 1.05 over a radial portion extending over the radially outer 20% of the blades.
    Type: Grant
    Filed: February 26, 2021
    Date of Patent: October 10, 2023
    Assignee: SAFRAN AERO BOOSTERS SA
    Inventor: Rémy Henri Pierre Princivalle
  • Device for distributing oil from a rolling bearing for an aircraft turbine engine
    Patent number: 11781446
    Abstract: Device for distributing oil from a rolling bearing (8) for an aircraft turbine engine, comprising: —a rolling bearing (8), —a body (5) for distributing oil, which body is configured to be mounted on a turbine engine shaft (4), said body comprising: i) a first outer cylindrical surface (5a) for mounting the inner ring (12) of the bearing, ii) a ring-shaped scoop (11) for recovering oil, iii) a ring-shaped track (26) of a dynamic seal (22), iv) a circuit (7) for lubricating the bearing and cooling the track, said circuit being formed in the body, characterised in that the ring-shaped scoop is the first scoop (11a) which supplies a first portion (7x) of the circuit with a view to cooling the track, and in that the body comprises a second ring-shaped scoop (11b) for recovering oil, which scoop supplies a second portion (7y) of the circuit with a view to lubricating the bearing.
    Type: Grant
    Filed: February 7, 2021
    Date of Patent: October 10, 2023
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Christoph Marcel Lucien Perdrigeon, Regis Eugene Henri Servant, Guillaume Francois Jean Bazin