Patents Assigned to SAFRAN AIRCRAFTS ENGINES
  • TURBOMACHINE MODULE EQUIPPED WITH AN ELECTRIC MACHINE, AND TURBOMACHINE EQUIPPED WITH SUCH A MODULE
    Publication number: 20240052789
    Abstract: An aircraft turbomachine module, including an accessory gearbox, a transfer shaft, and a drive shaft rotatably connected with one another by a power transmission device. The power transmission device can be housed in a gearbox and the module can further include an electric machine rotatably connected to the transfer shaft. The electric machine can be interposed between the transmission housing and at least one part the transfer shaft.
    Type: Application
    Filed: December 20, 2021
    Publication date: February 15, 2024
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Frédéric DAUTREPPE, Jean-Pierre Elie GALIVEL
  • AIRCRAFT TURBINE ENGINE ASSEMBLY COMPRISING A HOLDER FOR FITTINGS
    Publication number: 20240052788
    Abstract: Assembly for an aircraft turbine engine, comprising an intermediate casing hub, an accessory gearbox, and a transfer case including a power transmission shaft configured to transmit mechanical power, taken off an engine shaft of the turbine engine, to at least one accessory mounted on the accessory gearbox, in which the transfer case comprises a structural element surrounding the power transmission shaft and rigidly attaching the accessory gearbox to the intermediate casing hub.
    Type: Application
    Filed: December 15, 2021
    Publication date: February 15, 2024
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Bruno Albert BEUTIN, Anthony Pierre Guy DELAFORGE, Zoltan ZSIGA
  • Method for coating a turbomachine guide vane, associated guide vane
    Patent number: 11898466
    Abstract: A method for coating a turbomachine guide vane including a root and a tip, an extrados face and an intrados face connected to one another by a leading edge and a trailing edge, the method including completely covering one of the faces of the vane with a polymer coating of thickness (e1) provided with grooves, removing the grooves from a part of the polymer coating in such a way that the polymer coating includes a grooved zone and a non-grooved zone, coating the non-grooved zone with a coat of paint of thickness (e3) such that the thickness of the coat of paint superimposed on the non-grooved zone is substantially equal to the thickness (e1) of the grooved zone.
    Type: Grant
    Filed: June 18, 2020
    Date of Patent: February 13, 2024
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Célia Iglesias Cano, Vincent Marie Jacques Rémi De Carné-Carnavalet, Antoine Hubert Marie Jean Masson
  • Method for manufacturing a CMC part
    Patent number: 11897816
    Abstract: A process for manufacturing a part made of a ceramic matrix composite material, includes coating an outer surface of a porous preform with a layer of a fugitive material to form a model of the part to be obtained, the fugitive material being wax or resin, the fugitive material layer in the model not exceeding the highest peak of surface undulations of the preform, and ceramic and/or carbon particles being present in the porosity of the preform, coating the model formed with a ceramic powder composition, heat treating the coated model to remove the fugitive material and form a ceramic shell mold by sintering of the ceramic powder composition, introducing a molten composition including silicon into the shell mold to obtain the part in the shell mold, the molten composition infiltrating the porosity of the preform to form the ceramic matrix, and separating the shell mold from the part obtained.
    Type: Grant
    Filed: May 15, 2019
    Date of Patent: February 13, 2024
    Assignees: SAFRAN, SAFRAN CERAMICS, SAFRAN AIRCRAFT ENGINES
    Inventors: Michaël Podgorski, Bruno Jacques Gérard Dambrine, Emilie Chantal Gisèle Mendez, Wen Zhang, Yvan Rappart, Charles Leleu
  • Turbofan engine comprising an outlet cone cooled by its secondary flow
    Patent number: 11898517
    Abstract: A turbofan engine including an exhaust casing traversed by a primary flow and surrounded by a secondary flow and an outlet cone carried by this exhaust casing, the exhaust casing and the outlet cone together defining an internal space. The exhaust casing includes a hollow radial arm traversing the primary flow in order to convey part of the secondary flow so as to form a cooling flow for supplying the internal space, and the outlet cone is terminated by an opening for discharging the cooling flow.
    Type: Grant
    Filed: November 21, 2019
    Date of Patent: February 13, 2024
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Guillaume Claude Robert Belmon, Cédric Zaccardi
  • AUXILIARY OIL TANK FOR AN AIRCRAFT TURBINE ENGINE
    Publication number: 20240044289
    Abstract: An auxiliary tank for an aircraft turbine engine is provided, and in conjunction with a pump and associated auxiliary lubrication circuit, supplies oil to a reducer when, for example, a phase of free rotation of the fan is detected. Thus, the reducer is always lubricated, even during the phases of free rotation of the fan, thus ensuring a longer life of the reducer gears. The auxiliary tank is arranged with respect to the reducer so that oil is recovered from the reducer at least in part by the auxiliary tank.
    Type: Application
    Filed: October 23, 2023
    Publication date: February 8, 2024
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Christophe Paul Jacquemard, Didier Gabriel Bertrand Desombre
  • Composite-material casing having an integrated stiffener
    Patent number: 11891910
    Abstract: A method for manufacturing a composite-material casing for a gas turbine, includes producing by three-dimensional weaving a fiber texture in the form of a strip, winding of the fiber texture around several superimposed turns on a mandrel with a profile corresponding to that of the casing to be manufactured in order to obtain a fiber preform of a shape corresponding to that of the casing to be manufactured, and densifying the fiber preform by a matrix. During the winding of the last turn of the fiber texture on the mandrel, at least one stiffening element is interposed between the before-last turn and the last turn of the fiber texture. The stiffening element projects over the outer surface of the before-last turn of the fiber texture. The stiffening element has an axial section of omega-type shape.
    Type: Grant
    Filed: September 3, 2019
    Date of Patent: February 6, 2024
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Clément Bourolleau, Serge Domingues, Vincent Pascal Fiore, Florent Louis André Rognin, Anwer Siraj
  • Component of revolution made of composite material having improved resistance to delamination
    Patent number: 11890822
    Abstract: A process for manufacturing a cylindrical composite component comprises includes producing a fibrous texture in the form of a strip by three-dimensional or multi-layer weaving, winding the fibrous texture on several superimposed lathes on a mandrel with a profile corresponding to that of the component to be manufactured so as to form a fibrous preform, densifying the fibrous preform by a matrix. When the fibrous texture is wound on the mandrel, a web including a fugitive material filled with carbon nanotubes is interposed between the adjacent turns of the fibrous texture.
    Type: Grant
    Filed: June 18, 2020
    Date of Patent: February 6, 2024
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Didier Fromonteil, Laurent Jean Baptiste Baroumes, Hervé Grelin
  • Method and device for estimating a dead zone of a turbomachine discharge valve
    Patent number: 11891958
    Abstract: The invention relates to a method for estimating a dead zone at closing of a flap (P1) of a discharge valve (VBV1) of a turbomachine, in which the actual position of the actuator (V1) is measured for a setpoint closing signal of the flap (P1), a static angle is determined from the actual position, a closing dead zone is determined, corresponding to the fact that the joint (J1) is compressed so as to not let the primary flow pass through the orifice (O1) in the secondary flow, by the fact that the dead zone is equal to a reference dead zone, which has been predetermined on a reference turbomachine operating on the ground, to which the measured static angle has been added and from which a reference static angle, which has been predetermined on the reference turbomachine operating in flight, has been subtracted.
    Type: Grant
    Filed: May 15, 2020
    Date of Patent: February 6, 2024
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Sébastien Jean Fernand Deneuve, Jérôme Pascal Laurent Patrick Tronche
  • Turbofan comprising a power supply device to drive the compressor
    Patent number: 11891967
    Abstract: A turbofan includes a fan, a casing positioned downstream of the fan and separating a primary flowpath from a secondary flowpath, a compressor, a combustion chamber and a turbine being arranged in the primary flowpath, the turbofan having a differential transmission coupled to the turbine, and a power supply device configured to provide additional power to the one provided by the turbine to drive the compressor.
    Type: Grant
    Filed: September 20, 2019
    Date of Patent: February 6, 2024
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Henri Yesilcimen, Caroline Marie Frantz, Nicolas Jérôme Jean Tantot, Nathalie Nowakowski, Gilles Alain Marie Charier, Kévin Morgane Lemarchand, Jonathan Evert Vlastuin
  • Automatic blade pitch control
    Patent number: 11891919
    Abstract: The invention relates to a method for controlling a pitch angle of the vanes or blades of a propellant body of a turbine engine, comprising generating a pitch command (ifinal) according to a rotational speed of the propeller (XNmes) and a speed setpoint (XNcons), the method comprises a nominal regulating chain (13), wherein the pitch command is further generated according to a value of a pitch angle (?mes) of the vanes or blades of the propellant body, and an off-nominal regulating chain (16), wherein the pitch command is generated independently of a value of a pitch angle of the vanes or blades of the propellant body.
    Type: Grant
    Filed: March 5, 2021
    Date of Patent: February 6, 2024
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Sébastien Jean Fernand Deneuve, Charles Ying
  • Method for manufacturing a part made of composite material with compliance control
    Patent number: 11891342
    Abstract: Method for manufacturing a composite material part includes injecting a slurry containing a refractory ceramic particle powder into a fibrous texture, draining the liquid from the slurry that passed through the fibrous texture and retaining the refractory ceramic particle powder inside said texture so as to obtain a fibrous preform loaded with refractory ceramic particles, and demoulding of the fibrous preform. The method includes, after demoulding the fibrous preform, checking the compliance of the demoulded fibrous preform. If the preform is noncompliant, the method also includes, before a sintering, immersing the demoulded fibrous preform in a bath of a liquid suitable for decompacting the refractory ceramic particles present in the fibrous preform, and additionally injecting a slurry containing a refractory ceramic particle powder into the fibrous preform present in the mould cavity.
    Type: Grant
    Filed: October 4, 2019
    Date of Patent: February 6, 2024
    Assignees: SAFRAN AIRCRAFT ENGINES, SAFRAN
    Inventors: Ludovic Philippe Liais, Nicolas Droz, Michaël Podgorski
  • Variable-pitch stator vane for an aircraft turbine engine
    Patent number: 11891901
    Abstract: A variable-pitch stator blade includes an airfoil having a central portion with a first chord and a first skeleton line delimited by a leading edge and a trailing edge. An end portion has a second chord and a second skeleton line delimited by the leading edge and a downstream limit. A skeleton angle at a first length I1 of the first chord is defined by a function G1(l1), and the skeleton angle at a second length l2 of the second rope being chord is defined by a function G2(l2). The absolute value of the average increase A2 of G2?(l2) between the leading edge and the downstream limit is greater than the absolute value of the average increase Al of Gl?(l1) between the leading edge and a point P, wherein the first length I1 corresponds to the total length of the second chord.
    Type: Grant
    Filed: April 2, 2020
    Date of Patent: February 6, 2024
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Mickael Cavarec, Sébastien Claude Cochon, Pierre-Hugues Ambroise Maxime Victor Retiveau
  • Composite platform for a fan of an aircraft turbine engine
    Patent number: 11891913
    Abstract: A composite platform for a fan of an aircraft turbine engine. The platform includes an elongate wall and is configured to extend between two fan blades. The wall includes an aerodynamic outer surface and an inner surface, on which a fastening tab is located, wherein the fastening tab is configured to be attached to a fan disc. The fastening tab is integrally formed with a metal reinforcement which has a plate having an elongate shape and which extends over more than 50% of the longitudinal extent of the wall, the wall being produced by overmolding a resin on the plate so as to be integrated into the wall.
    Type: Grant
    Filed: February 19, 2021
    Date of Patent: February 6, 2024
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Matteo Minervino, Didier Fromonteil, Hervé Grelin, Damien Bruno Lamouche
  • TURBINE BLADE FOR AN AIRCRAFT TURBOMACHINE, PROVIDED WITH A CHANNEL FOR EJECTING A PRIMARY FLOW TOWARDS AN INTER-LIP CAVITY
    Publication number: 20240035391
    Abstract: A blade and a sealing element forming an assembly for a turbomachine turbine. The blade includes an airfoil and a platform to which the sealing element is connected. An internal channel passes through the platform so as to draw off fluid circulating in a primary duct that it delimits and to inject the thus drawn-off fluid into an inter-lip cavity delimited by the sealing element.
    Type: Application
    Filed: December 1, 2021
    Publication date: February 1, 2024
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Jean Charles Marie COUSSIROU, Thomas LANGEVIN, Benoit Guillaume SILET
  • TURBOMACHINE ROTOR HAVING IMPROVED VIBRATORY BEHAVIOUR
    Publication number: 20240035385
    Abstract: Assembly comprising a body extending around a central axis, the body having an outer surface from which a plurality of blades extend, each of said blades having a blade root and a blade tip, defining an inner radial end and an outer radial end of the blade relative to the central axis, said blades having the same blade height measured radially relative to the central axis, characterized in that each of the blades is connected to the body by its blade root via a connection having a nonzero connection height, so that for the plurality of said blades, the connection height of two successive blades is different.
    Type: Application
    Filed: February 1, 2022
    Publication date: February 1, 2024
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Sylvain PHOURATSAMAY, Sylvain Frédéric AVAKIAN, Mickael CAVAREC
  • Recovery of lubricating oil from a reduction gear of an aircraft turbine engine
    Patent number: 11885265
    Abstract: Aircraft turbine engine (10), comprising:—at least one first turbine rotor (22a) connected to a first turbine shaft (36) and comprising rotor blades located in a stream (V),—an annular exhaust casing (28) supporting at least one bearing (60, 62) for guiding the rotation of the first shaft and comprising arms (28a) located in the stream, downstream of the blades, and—a mechanical planetary gearbox (42) which comprises a sun gear (44), a ring gear (40) and a planet carrier (46), the gearbox being at least partially surrounded by the exhaust casing and one of the rotatable elements chosen from the sun gear and the ring gear being connected to the first shaft, characterised in that the exhaust casing carries a device (70) for recovering and discharging oil projected centrifugally by the reduction gear.
    Type: Grant
    Filed: December 1, 2020
    Date of Patent: January 30, 2024
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Paul Ghislain Albert Levisse, Olivier Belmonte, Amelie Argie Antoinette Chassagne
  • Turbomachine rotary fan blade, fan, and turbomachine provided therewith
    Patent number: 11885239
    Abstract: The invention relates to a turbomachine rotary-fan blade having a predetermined breaking zone, which extends from the upstream edge along a given length and from the blade-tip edge over a given height. According to the invention, the body is made of a composite material comprising a fibre reinforcement obtained by three-dimensional weaving of warp and weft strands, and a resin matrix in which the fibre reinforcement is embedded, and has, in or in the vicinity of the zone, a discontinuity of at least some of the strands, configured such that the zone partially detaches when there is tangential friction in the thickness direction against the blade-tip edge, the height being less than 3% of the aerodynamic stream height of the blade.
    Type: Grant
    Filed: November 18, 2020
    Date of Patent: January 30, 2024
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Guillaume Pascal Jean-Charles Gondre, Thomas Alain De Gaillard, Pierre Jean Faivre D'Arcier
  • Assembly for a turbine engine
    Patent number: 11885268
    Abstract: An assembly for a turbine engine extending along an axis, includes a stator, a low-pressure compressor shaft, a low-pressure compressor comprising a rotor comprising a drum rotatably coupled to the shaft of the low-pressure compressor, and a fan comprising a disk rotatably coupled to the shaft of the low-pressure compressor. The drum has a radially internal part rotatably coupled to the shaft of the low-pressure compressor and a radially external part fixed to the radially internal part by means of detachable fixing means. A first axial retention means is configured to axially and detachably retain the disk of the fan relative to the shaft of the low-pressure compressor. A second axial retention means is configured to axially and detachably retain the radially internal part of the drum relative to the shaft of the low-pressure compressor.
    Type: Grant
    Filed: January 6, 2021
    Date of Patent: January 30, 2024
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Philippe Gérard Edmond Joly, Jean-Marc Claude Perrollaz, Laurent Jablonski
  • Thrust reverser cascade including acoustic treatment
    Patent number: 11885280
    Abstract: A cascade type thrust reverser device for a turbomachine of an aircraft, comprising a thrust reverser cascade and a casing, the cascade including first cavities, and the casing comprising an opening defining a housing wherein said cascade can be inserted in a first direction, and the casing and said cascade being in relative translation with respect to one another in the first direction between a first position of the device in which the cascade is entirely positioned in the housing and a second position of the device in which said cascade is at least partially outside said housing. The casing comprises an acoustic treatment panel including second cavities extending in a second plane parallel to the first plane, each first cavity facing a second cavity when the device is in the first position to form an acoustic treatment cell.
    Type: Grant
    Filed: April 3, 2020
    Date of Patent: January 30, 2024
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Norman Bruno André Jodet, Jéremy Paul Francisco Gonzalez