Patents Assigned to SAFRAN AIRCRAFT ENGINES
  • Device for damping a rolling bearing, comprising a rigid support passing through a flexible cage
    Patent number: 11867236
    Abstract: A device for damping a rolling bearing includes a support and a radially flexible cage. The cage includes a ring provided in order to be mounted on the periphery of a rolling bearing. The radial flexibility of this cage results from the structure thereof which is perforated by oblique posts connecting the ring to an attachment annulus of this cage. The support includes a plurality of teeth each extending radially through a respective inter-post opening of the cage. The ring and the support form, radially between one another, a fluid damping cavity suitable for forming a compressed fluid film. The device allows a controlled radial movement of the ring, the latter being radially limited by the support, while having a limited footprint.
    Type: Grant
    Filed: June 16, 2020
    Date of Patent: January 9, 2024
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventor: Daniel Georges Plona
  • Turbine nozzle having blading made of ceramic matrix composite through which a metal ventilation circuit passes
    Patent number: 11867091
    Abstract: A nozzle for a turbomachine turbine. The nozzle includes blades made of ceramic matrix composite material, and at least one metal liner passing through a respective blade. The liner is connected in a sealed manner to a metal internal shroud so as to guide a ventilation fluid through the blade. The nozzle can be configured to maintain effective sealing in spite of the different thermal expansions of the blade and of the internal shroud.
    Type: Grant
    Filed: October 1, 2020
    Date of Patent: January 9, 2024
    Assignees: SAFRAN AIRCRAFT ENGINES, SAFRAN CERAMICS
    Inventors: Clément Jarrossay, Sébastien Serge Francis Congratel, Aurélien Gaillard, David René Pierre Le Cair, Matthieu Arnaud Gimat
  • Blade for a rotating bladed disk for an aircraft turbine engine comprising a sealing lip having an optimized non-constant cross section
    Patent number: 11867065
    Abstract: To increase the inertia of a sealing lip of a blade for an aircraft turbine engine, and thus improve the service life of such a sealing lip, the sealing lip is conformed so as to have a trough in the outer surface thereof and a corresponding boss in the inner surface thereof, the trough and the boss being defined based on a connection cross section of the sealing lip to a blade body, and being formed at a distance from a free axial end of the sealing lip.
    Type: Grant
    Filed: February 11, 2021
    Date of Patent: January 9, 2024
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Edouard Emmanuel Garreau, Josserand Jacques Andre Bassery, Lucas Geoffrey Desbois, Etienne Leon Francois, Samuel Laurent Noel Mathieu Juge, Elsa Maxime, Ba-Phuc Tang, Denis Gabriel Trahot, Thomas Tsassis
  • System for lubricating an aeronautical engine
    Patent number: 11867076
    Abstract: The invention relates to a system (1) for lubricating an aeronautical engine (5) and a reduction gearbox (4) associated with the engine (5), the system (1) comprising an oil reservoir (2) feeding at least one first supply pump (3) supplying a first circuit (6) of the gearbox (4) opening into at least one chamber (4a) of the gearbox (4) and, in parallel, a second circuit (7) of the engine (5) opening into chambers (5a) of the engine (5). The second circuit (7) comprises a jet pump (9) of variable cross section supplied at least by the first supply pump (3), bypassing the first circuit (6), a second driven supply pump (10) being integrated into the second circuit (7) downstream of the jet pump (9), a portion of a flow (Qp) in the first circuit (6) being drawn off by the jet pump (9) to supply the second circuit (7).
    Type: Grant
    Filed: May 18, 2020
    Date of Patent: January 9, 2024
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Loic Pora, Huguette De Wergifosse
  • BLADE COMPRISING A SHIELD HAVING A DEFROSTING AIR PASSAGE DUCT
    Publication number: 20240003265
    Abstract: The invention relates to a blade comprising a shield (14) attached to the upstream end of the body of the blade, the shield (14) comprising an upstream end forming a leading edge of the blade, the shield (14) further comprising a nose (141) upstream from which the leading edge is located, an pressure-face fin and an suction-face fin laterally attached on the blade, the fins extending from the nose, the blade comprising a defrosting air passage duct (15) arranged inside the nose and extending radially inside the nose, the duct (15) having an inner end (151) emerging opposite the root (125) and a radially external end emerging from the nose between the leading edge and its junction at the pressure-face fin.
    Type: Application
    Filed: November 10, 2021
    Publication date: January 4, 2024
    Applicant: Safran Aircraft Engines
    Inventors: Guillaume Pascal Jean-Charles GONDRE, Morgane Astrid LEGER, Stéphane Roger MAHIAS, Romuald Bernard MAUVAIS
  • COMPOSITE PART, IN PARTICULAR FOR AN AIRCRAFT TURBINE ENGINE
    Publication number: 20240003260
    Abstract: A part made of composite material, in particular for an aircraft turbine engine, includes a body produced from fibers woven in three dimensions and immersed in a resin, in particular an organic or polymer resin. The part has at least one crack sensor capable of detecting a crack in the part, at least one link element connected to the sensor and configured to transmit a signal (S), in particular to a member outside of the part, when a crack in the part is detected. The crack sensor has at least one conductive wire woven with the fibers of the body, and the link element is configured to measure the resistance of the conductive wire and to wirelessly transmit the signal.
    Type: Application
    Filed: November 17, 2021
    Publication date: January 4, 2024
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Tony Alain Roger Joël LHOMMEAU, Damien Bruno LAMOUCHE, Mattéo MINERVINO, Julie Valérie Clara LAVIGNE
  • AIRCRAFT TURBINE ENGINE ASSEMBLY COMPRISING A PASSIVE VALVE FOR BY-PASSING A FUEL/OIL HEAT EXCHANGER
    Publication number: 20240003299
    Abstract: An aircraft turbine engine assembly, including a lubricating oil circuit and a fuel supply device, the assembly also including a passive bypass valve enabling the oil to bypass an exchanger, the valve including a valve body and a piston arranged to move in a sliding space defining a first actuating chamber supplied with oil from the oil circuit, as well as a second actuating chamber supplied with fuel from the device, the valve being configured so that when the differential pressure between the oil pressure in the first actuating chamber and the fuel pressure in the second actuating chamber drops below a predetermined value of differential pressure, the piston moves from a normal operating position to an exchanger bypass position.
    Type: Application
    Filed: November 30, 2021
    Publication date: January 4, 2024
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Sébastien ORIOL, Nicolas Vincent Pierre-Yves COTEREAU, Mohammed-Lamine BOUTALEB
  • IMPROVED TURBINE RING ASSEMBLY
    Publication number: 20240003267
    Abstract: A turbine ring assembly extending around a longitudinal axis and comprises: a plurality of ring angular sectors made of CMC material circumferentially arranged in such a way as to form a turbine ring, each sector comprising a base from which an upstream leg and a downstream leg extend radially, a ring support structure comprising: a spacer extending around the sectors and comprising a downstream flange in such a way that the downstream leg of each sector is held against the downstream flange, a upstream force-absorbing plate extending circumferentially around the longitudinal axis in such a way as to be in contact with the upstream leg of each sector and fixed to an upstream area of the spacer which extends in extension of the upstream leg.
    Type: Application
    Filed: November 4, 2021
    Publication date: January 4, 2024
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Clément Emile André CAZIN, Pascal Cédric TABARIN, Sébastien Serge Francis CONGRATEL, Nicolas Paul TABLEAU
  • AIRCRAFT TURBINE ENGINE DRIVE LINE SHAFT COMPRISING A CONNECTING RING FOR DISASSEMBLING THE DRIVE LINE
    Publication number: 20240003258
    Abstract: Disclosed is a main shaft for an aircraft turbine engine drive line extending longitudinally from front to rear along an axis and having a rear portion configured for receiving a front portion of a rear shaft by interlocking, the main shaft having: —a front retaining member and a rear retaining member together defining a prison and each having a central opening, —a connecting ring, located in the prison, having a rear end configured to be screwed to a front end of the rear shaft extending into the central opening of the rear retaining member, the connecting ring having a gripping member formed on the inner surface and accessible from a front portion of the main shaft by a tool extending via the central opening of the front retaining member.
    Type: Application
    Filed: November 8, 2021
    Publication date: January 4, 2024
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Christophe Paul Jacquemard, Xavier Jean Yves Alain Agneray
  • Aircraft turboshaft engine compressor comprising a device for immobilising a retaining annulus
    Patent number: 11859508
    Abstract: Disclosed is a compressor of a dual-flow aircraft turboshaft engine extending longitudinally along an axis X, the compressor comprising a low-pressure compressor, a high-pressure compressor and an intermediate casing axially connecting the low-pressure compressor and the high-pressure compressor, the high-pressure compressor comprising an inlet guide stator comprising a retaining ring, an outer high-pressure compressor casing and a plurality of vanes, the compressor comprising an immobilising device comprising at least one first member secured to the intermediate casing and at least one second member secured to the retaining ring and configured to cooperate with the first member in order to prevent tangential movement while allowing axial movement and radial movement of the retaining ring relative to the intermediate casing according to the axis X.
    Type: Grant
    Filed: July 10, 2020
    Date of Patent: January 2, 2024
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Thomas Nolwenn Emmanuel Delahaye, Blaise Bergon, Laurent Jablonski, Lilian Yann Dumas, Thomas Etienne Camille Marie Van De Kerckhove, Noël Joseph Camille Robin, Guillaume Sevi
  • Moving blade for a wheel of a turbine engine
    Patent number: 11859513
    Abstract: A moving blade for a wheel of an aircraft turbine engine, including an aerodynamic aerofoil and an outer heel defining the aerofoil. The heel includes a platform and a first lip that projects from the platform. The first lip is inclined upstream and peripherally along an axis of elongation. The heel includes a row of ribs that are arranged at a distance from each other. The row of ribs extends along the axis of elongation and from the platform up to the first lip. The ribs are arranged upstream of the first lip in such a way as to generate turbulence upstream of first lip.
    Type: Grant
    Filed: September 13, 2019
    Date of Patent: January 2, 2024
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Raphael Jean Philippe Dupeyre, Josserand Jacques Andre Bassery, Jeremy Jacques Attilio Fanelli, Etienne Leon Francois
  • Profiled structure and associated turbomachine
    Patent number: 11859534
    Abstract: An airflow profiled structure having a profiled leading edge. The profiled leading edge having, along a leading edge line, a serrated profile line with a succession of teeth and depressions. The airflow profiled structure also includes a porous acoustically absorbent region located towards the bottom of the depressions.
    Type: Grant
    Filed: February 15, 2019
    Date of Patent: January 2, 2024
    Assignee: Safran Aircraft Engines
    Inventors: Fernando Gea Aguilera, Mathieu Simon Paul Gruber, Georges Jean Xavier Riou
  • Device for driving a generator of an aircraft turbomachine and method for regulating the speed of such a generator
    Patent number: 11859558
    Abstract: A device for driving an integrated generator from an accessories relay box of a turbomachine. The device includes first and second electric motors arranged to transfer electric power from one to the other, one or more controllers configured for controlling said electric motors, and an epicyclic reduction gear train. The gear train includes a first element intended to be coupled to the accessories relay box, a second element intended to be coupled to the generator, and a third element driven to rotate by said first electric motor. The control means are configured to modify the speed of rotation of the third element in such a way that the second element is driven to rotate at a constant speed.
    Type: Grant
    Filed: July 23, 2020
    Date of Patent: January 2, 2024
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventor: Huguette De Wergifosse
  • Variable-pitch stator vane comprising aerodynamic fins
    Patent number: 11859502
    Abstract: A variable-pitch stator vane for a turbine engine compressor stator, extending in a longitudinal radial plane including a radially inner plate and a radially outer plate between which at least one blade extends, each plate including a transverse longitudinal wall facing the other plate, characterised in that the transverse longitudinal wall of at least one plate includes at least one fin protruding radially towards the other plate.
    Type: Grant
    Filed: October 1, 2020
    Date of Patent: January 2, 2024
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventor: Christophe Scholtes
  • MODULARITY OF AN AIRCRAFT TURBOMACHINE
    Publication number: 20230417192
    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: Application
    Filed: November 2, 2021
    Publication date: December 28, 2023
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Paul Ghislain Albert LEVISSE, Olivier BELMONTE
  • METHOD FOR CONTROLLING A TURBOMACHINE COMPRISING AN ELECTRIC MOTOR
    Publication number: 20230417194
    Abstract: The invention relates to a method for controlling a turbine engine having an electric motor forming a device for injecting torque on the high-pressure rotation shaft, in which method a setpoint for fuel flow into the combustion chamber and a setpoint for torque supplied to the electric motor are determined, the control method having: a step of determining a temperature correction value as a function of a temperature parameter of the gases leaving the turbine engine and a maximum value of the temperature parameter of the gases leaving the turbine engine, a step of determining a torque correction value as a function of the temperature correction value and a step of determining the torque setpoint as a function of the torque correction value.
    Type: Application
    Filed: November 12, 2021
    Publication date: December 28, 2023
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventor: Cedrik Djelassi
  • Aircraft turbine engine comprising variable-pitch propeller blades
    Patent number: 11851157
    Abstract: A system for controlling the pitch of a propeller blade for an aircraft turbine engine, including a cup having an annular wall extending about an axis intended to be a pitch setting axis of the blade, and a bottom wall configured so as to cooperate in a form-fitting manner with a free end of the root so that the cup is prevented from rotating relative to the root about the axis, and a locking ring that is configured so as to be mounted within the cup and to cooperate respectively with the root and the annular wall of the cup in order to ensure axial retention of the root in the cup.
    Type: Grant
    Filed: July 15, 2021
    Date of Patent: December 26, 2023
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Vincent Joudon, Clément Cottet, Vivien Mickaël Courtier, Régis Eugène Henri Servant
  • Aircraft turbomachine arrangement comprising a lubrication pump driven by two oblique gears
    Patent number: 11852079
    Abstract: A pump that can be a gear pump that drives a rotating body of an aircraft turbine engine such as a fan shaft, is set in rotation always in the same direction, by virtue of a transmission including an oblique double gear formed by a toothed wheel on the same side as the rotating body and meshing with two pinions connected to a shaft driving the pump through free-wheels with identical driving directions, whereas the pinions have opposite directions of rotation.
    Type: Grant
    Filed: June 16, 2020
    Date of Patent: December 26, 2023
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Emmanuel Fabrice Marie Baret, Julien Fabien Patrick Becoulet, Franck Emmanuel Bosco, Michel Gilbert Roland Brault, Paul Ghislain Albert Levisse
  • Fire resistance device designed to be placed between one end of a mounting strut for an aircraft turbomachine and a cowling of said turbomachine delimiting an inter-flow compartment
    Patent number: 11851200
    Abstract: A fire resistance device designed to be placed between a mounting strut of a double-flow aircraft turbomachine and a connecting cowling with which the turbomachine is equipped, the connecting cowling being designed to connect an upstream ring, delimiting an inter-flow compartment, to an arm that extends radially across a secondary flow of the turbomachine. The device can be produced as a single piece and includes two contact lips which extend along different lines, the first lip having a C-shaped cross-section.
    Type: Grant
    Filed: June 25, 2019
    Date of Patent: December 26, 2023
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Bruno Alexandre Didier Jacon, Baghdad Achbari, Hervé Simonotti
  • Turbomachine with device for cooling and pressurising a turbine
    Patent number: 11852025
    Abstract: A turbo machine including a device for ventilating and pressurising a turbine rotor of a turbomachine having an axis, the device including at least one collection pipe suitable for collecting a fraction of the air circulating in a high-pressure compressor of the turbomachine and conveying it to a first inner chamber inside the turbomachine that communicates with a second inner chamber delimited by the turbine rotor, the first and second chambers being at least partially separated by a stationary shroud having the axis, wherein it includes at least one injector passing through the stationary shroud and having a cross-section that varies in response to a pressure difference between the first and second chambers.
    Type: Grant
    Filed: March 15, 2021
    Date of Patent: December 26, 2023
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Paco Maurer, Fabien Roger Gaston Caty