Patents Assigned to SAFRAN AIRCRAFT ENGINES
  • Publication number: 20240102397
    Abstract: A turbine stator assembly including a guide vane assembly and a sealing ring bearing an abradable element of a dynamic sealing ring. The assembly includes pins secured to the sealing ring and cooperating with respective oblong openings formed in the guide vane assembly so as to allow a radial movement of the ring with respect to the guide vane assembly in order to compensate for differential thermal expansions. A seal is arranged so as to compensate for circumferential spaces between ring sectors forming the guide vane assembly.
    Type: Application
    Filed: December 3, 2021
    Publication date: March 28, 2024
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Patrick Jean Laurent SULTANA, Marc-Antoine Anatole GOT, Laurent Cédric ZAMAI
  • Publication number: 20240101264
    Abstract: An acoustic treatment panel including acoustic absorption cells each comprising a bottom wall, a porous inlet wall, an enclosure extending in an axial direction between the bottom wall and the inlet wall, and a first acoustic horn extending inside the enclosure between a first opening and a second opening that is smaller than said first opening, the first opening facing said inlet wall. Each cell comprises a second horn extending inside the enclosure in the first axial direction between a first opening of the second horn and a second opening of the second horn that is smaller than said first opening.
    Type: Application
    Filed: December 14, 2021
    Publication date: March 28, 2024
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Georges Jean Xavier RIOU, Fernando GEA AGUILERA
  • Patent number: 11939936
    Abstract: A cascade type thrust reverser device for a turbomachine of an aircraft, comprising a cascade including first partitions, second partitions intersecting the first partitions, and cavities, and a casing including a housing into which the cascade can be inserted in a first direction, the casing and the cascade being in relative translation with respect to one another in the first direction. The casing comprises a perforated wall intended to be in contact with an air flow and including orifices and wall strips with no orifices and intended to face the first walls of the cascade when the device is in a first position in which the cascade is entirely positioned in the housing.
    Type: Grant
    Filed: April 3, 2020
    Date of Patent: March 26, 2024
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Norman Bruno André Jodet, Jéremy Paul Francisco Gonzalez
  • Patent number: 11939937
    Abstract: The invention relates to a method for manufacturing a composite platform (30) for a fan of an aircraft turbine engine, wherein said platform comprises an elongate wall (32) and is configured to extend between two fan blades (3), said wall comprising an outer aerodynamic surface (32a) and an inner surface (32b), on which a fastening tab is located (34), said fastening tab being configured to be fixed to a fan disc (2). The invention is characterized in that it comprises the steps of: a) preparing fabrics or sheets which are pre-impregnated with a resin, b) depositing the fabrics or sheets in a mold, c) positioning a metal reinforcement (36) in the mold on the fabrics or sheets, the reinforcement being integrally formed with said fastening tab, d) depositing the fabrics or sheets on a part of the reinforcement, and e) closing and heating the mold for solidification of the assembly formed by the fabrics or sheets and the reinforcement.
    Type: Grant
    Filed: March 1, 2021
    Date of Patent: March 26, 2024
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Matteo Minervino, Didier Fromonteil, Hervé Grelin, Damien Bruno Lamouche
  • Patent number: 11939933
    Abstract: In a thrust reverser for an aircraft propulsion unit, the thrust reverser includes an internal fixed structure, a mobile cowl and blocking flaps. The thrust reverser also includes a first actuation mechanism that is configured to move the mobile cowl between a closing position and an opening position so as to cause the blocking flaps to move respectively between a retracted position and a deployed position, thus causing the thrust reverser to pass respectively between a full-thrust configuration and a thrust-reversal configuration. The thrust reverser also includes a second actuation mechanism that is configured to move the blocking flaps between the retracted position and a partially deployed position when the mobile cowl is in the closing position, so as to cause the thrust reverser to pass respectively between the full-thrust configuration and a reduced-thrust configuration.
    Type: Grant
    Filed: June 9, 2020
    Date of Patent: March 26, 2024
    Assignees: SAFRAN NACELLES, SAFRAN AIRCRAFT ENGINES
    Inventors: Denis Guillois, Florent Matthieu Jacques Nobelen, Luigi Bisanti
  • Publication number: 20240093611
    Abstract: The invention relates to a fan blade (3) made of composite material the fibrous reinforcement of which comprises first strands (12) having a first stiffness, second strands (13) having a second stiffness and third strands (14) having a third stiffness lower than the first stiffness and greater than the second stiffness, the blade comprising a first portion (15) comprising only first strands (12), a second portion (16) comprising only second strands (13) and a third portion (17) which is located between the first and second portions (15, 16) and which comprises both first, second and third strands (12, 13, 14); there is a gradual transition of properties at the interface between the different portions (15, 16, 17).
    Type: Application
    Filed: November 29, 2021
    Publication date: March 21, 2024
    Applicant: Safran Aircraft Engines
    Inventors: Carole Onja RAKOTOARISOA, Teddy FIXY, Guillaume Pascal Jean-Charles GONDRE, Julien Paul SCHNEIDER-DIE-GROSS
  • Publication number: 20240093616
    Abstract: An inner ring for supporting variable-pitch blades of an axial compressor stator of a turbomachine includes two or more ring sectors, assembled to form the inner ring, each ring sector including plural housings for receiving a pivot axis of one of the blades. At each junction plane between the ends of two successive ring sectors, an assembly pin and a cavity for receiving the assembly pin are engaged. The assembly pin is fixed on one end one of the two successive ring sectors and the cavity is formed at the end of the other of the two successive ring sectors. The cavity receives the assembly pin with a mounting clearance allowing a mounting by sliding fit, and the assembly pin is made of a material having a coefficient of thermal expansion greater than a coefficient of thermal expansion of a material constituting the successive ring sectors.
    Type: Application
    Filed: February 2, 2022
    Publication date: March 21, 2024
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventor: Nicolas Gérard Bénito CORNEC
  • Publication number: 20240093619
    Abstract: A turbine ring assembly extending around an axis, including a plurality of ring sectors made of ceramic matrix composite material forming a turbine ring and a ring support structure held by a turbine casing, each ring sector including a base from which an upstream tab and a downstream tab extend radially outward, spaced axially from one another, wherein the assembly also includes a cross-member mechanically connected to the ring support and including a first radial flange bearing against the upstream latching tabs of the ring sectors, and, for each ring sector, at least two transverse pins and a radial spring, each transverse pin passing through the upstream latching tab and the downstream latching tab of the ring sector and the ring support to hold the ring sector and the ring support secured to one another.
    Type: Application
    Filed: April 12, 2022
    Publication date: March 21, 2024
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Jérôme Claude George LEMONNIER, Franck Davy BOISNAULT, Florian Armand Gabriel GAUDRY, Kévin Claude Luc BAUDY, Marion France CHAMBRE
  • Publication number: 20240093638
    Abstract: A counter-rotating turbine for a turbine engine comprising an inner rotor having an inner drum to which is attached a plurality of inner impellers rotatably supported by a first shaft, an outer rotor comprising an outer drum to which is fastened a plurality of outer impellers rotatably supported by a second shaft coaxial with the first shaft, the outer rotor comprising a downstream impeller having a plurality of downstream moving blades extending between an outer shroud and an inner shroud, one upstream end of the outer shroud being attached downstream of said outer drum, the inner shroud being attached to the second shaft, at least one of the inner shroud and of the outer shroud comprising at least one flexible transition part configured to allow elastic deformation of said shroud in the radial direction.
    Type: Application
    Filed: October 8, 2020
    Publication date: March 21, 2024
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Simon Jean-Marie Bernard COUSSEAU, Mathieu Patrick Henri DELALANDRE, Patrick Jean Laurent SULTANA, Laurent Cédric ZAMAI
  • 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
  • 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
  • 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
  • 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
  • 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
  • Patent number: 11933497
    Abstract: The invention relates to an air/fuel injection system for a turbomachine, comprising:—an injector comprising a duct and an injection nose, arranged inside said duct, which extends from upstream to downstream along a longitudinal axis;—a mixer device comprising a bowl comprising an annular inlet, forming the inlet of the mixer device, from which there extends a conical portion flared in the downstream direction, said mixer device being arranged downstream of the injection nose; the injection system being characterized in that the injector comprises an air-injection annulus extending from the duct and from which there extends a connection ring comprising a divergent portion, said ring being arranged externally around the annular inlet of the mixer device.
    Type: Grant
    Filed: November 24, 2020
    Date of Patent: March 19, 2024
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Romain Nicolas Lunel, Haris Musaefendic
  • 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
  • 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
  • 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
  • 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
  • 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