Patents Assigned to SAFRAN AIRCRAFT ENGINES
  • Fuel supply circuit for a combustion chamber of a turbomachine
    Patent number: 11905885
    Abstract: A fuel supply circuit including a supply duct in which a first flow (Fl) is able to circulate, at least one supply pump for circulating the fuel from a tank to a metering unit, and a recirculation duct for a second flow upstream of the pump, wherein the ducts (20, 60) discharge in different directions upstream of the pump; the circuit includes a dispensing device including an internal flow duct for the first flow (Fl), an external flow channel for the second flow and at least one passage orifice for the second flow, which communicates fluidically with the channel; and the at least one orifice (810) and the duct are coaxial and respectively discharge upstream of the pump.
    Type: Grant
    Filed: October 5, 2021
    Date of Patent: February 20, 2024
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Kevin Didier Pierre Le Normand, Frederic Brettes, Loic Pora
  • Method for manufacturing a turbomachine compressor blade by compacting
    Patent number: 11904420
    Abstract: The invention relates to a method for producing a turbomachine compressor blade, comprising the following steps:—installing primary pins (26) comprising a material other than a titanium-based alloy in primary bores (20) of a core, the primary bores forming at least one polygon, and installing a secondary pin made of titanium-based alloy in a secondary bore of the core; —producing a stack (2) of a suction-face sheet (4), a core (14) and a pressure-face sheet (6); —compacting the stack; —removing the primary pins (26) from the primary bores (20); —removing the secondary pin from the secondary bore; and—taking the core (14) away from the stack.
    Type: Grant
    Filed: September 30, 2021
    Date of Patent: February 20, 2024
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Jérôme Salmon, Alexandre Gimel, Christophe Gleize, Axel Pereira, Jean François Richard
  • Fuel supply circuit for a combustion chamber of a turbomachine
    Patent number: 11905883
    Abstract: The invention relates to a fuel supply circuit (1) for a combustion chamber (2) of a turbomachine (10), comprising: —a fuel supply pump (3) configured to provide a fuel flow at a predetermined flow rate, —a plurality of fuel injectors (4), and —a ramp (5) for connecting the pump (3) to the injectors (4), said circuit further comprising a device for the heat treatment of the fuel (6), having a chamber (60) connected to a fuel inlet (61) linked to the pump (3) and to a fuel outlet (62) linked to the ramp (5), wherein heating elements (60) are located in said chamber and are configured to heat the fuel flow to a predetermined temperature so as to cause coking of the fuel within the chamber (60) of the device (6).
    Type: Grant
    Filed: January 13, 2021
    Date of Patent: February 20, 2024
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventor: Nicolas Marie Keruzore
  • Aircraft turbomachine with reducer
    Patent number: 11905889
    Abstract: A turbomachine includes a single ducted fan including a first shaft rotated by a second shaft via a speed reduction gearset, the second shaft being rotated by a third shaft of a turbine, the first shaft being guided in rotation with respect to a fixed structure via a first bearing and a second bearing placed upstream of the speed reduction gearset. The second shaft is guided in rotation with respect to the first shaft via a rolling bearing placed upstream of the speed reduction gearset, the rolling bearing comprising an outer ring housed in the first shaft, an inner ring connected to the second shaft and rolling elements arranged between the inner and outer rings.
    Type: Grant
    Filed: September 19, 2019
    Date of Patent: February 20, 2024
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Marion Jeanne Pierrette Verdier, Yanis Benslama, Michel Gilbert Roland Brault, Romain Guillaume Cuvillier, Serge René Morreale
  • Attachment of an acoustic shroud to a housing shell for an aircraft turbine engine
    Patent number: 11905839
    Abstract: The invention relates to a method for manufacturing an aircraft turbine engine housing, the housing (23) comprising: —an annular shell (29) with axis A; —an annular element (24; 253, 254) attached to the inside of the shell (29), the annular element comprising a body (25) made of NIDA-type cellular material and comprising a downstream portion (252) covered with an abradable material (26), and an upstream portion (251) without abradable material, the body (25) extending in a continuous manner from the upstream portion (251) to the downstream portion (252), the method comprising: —manufacturing the annular element in the form of a continuous annular body, —cutting the annular body into segments (253, 254), —attaching the segments to the shell, and —depositing the abradable material (26) onto the inside surface (25a) of the downstream portion (252).
    Type: Grant
    Filed: September 9, 2020
    Date of Patent: February 20, 2024
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Thomas Dupays, Clement Bourolleau, Coline Poulenc, Anwer Siraj
  • METHOD FOR PROCESSING VOLUME IMAGES BY PRINCIPAL COMPONENT ANALYSIS
    Publication number: 20240054631
    Abstract: Method for processing a plurality of X-ray tomography volume images each associated with a part, the plurality of volume images comprising a reference volume image, including: a step of correlating volume images to obtain a displacement field between each image and the reference image, to obtain a plurality of displacement fields minimizing the difference between the volume images, a processing by a dimensionality reduction method of the plurality of the image displacement fields to express them according to eigenmodes, and a statistical analysis of the fields expressed according to the eigenmodes.
    Type: Application
    Filed: December 24, 2021
    Publication date: February 15, 2024
    Applicants: SAFRAN, SAFRAN AIRCRAFT ENGINES, ECOLE NORMALE SUPERIEURE PARIS- SACLAY, CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE
    Inventors: Julien Paul SCHNEIDER-DIE-GROSS, Clément JAILIN, Arturo MENDOZA QUISPE, Stéphane ROUX
  • 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
  • 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
  • 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
  • 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
  • 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
  • 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
  • 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
  • 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
  • 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
  • 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