Patents Assigned to SAFRAN
  • 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
  • BISTABLE ELECTROMAGNETIC ACTUATOR AND AIRCRAFT BRAKE VALVE PROVIDED WITH SUCH AN ACTUATOR
    Publication number: 20230420169
    Abstract: The invention provides a bistable electromagnetic actuator comprising a yoke extending in part around a pivot axis of the actuator, an excitation coil supported by the yoke in order to generate control magnetic flux, a rotor movable about the pivot axis of the actuator and suitable for being held stationary in two stable angular positions as a function of the magnetic flux generated by the coil, an actuator member coupled to the rotor in order to form an assembly that can be turned, and a manual control device including a drive shaft dynamically coupled to the rotor in such a manner that turning the drive shaft causes the rotor to turn.
    Type: Application
    Filed: November 10, 2021
    Publication date: December 28, 2023
    Applicant: SAFRAN LANDING SYSTEMS
    Inventors: Laurent MONSAINT, Julien GLINEC, Guillaume DURAND, Mathieu GENGOUX
  • CONSOLE FOR A SEAT UNIT PROVIDED WITH A MOVABLE CLOSING PLATE FOR A STORAGE HOUSING
    Publication number: 20230415896
    Abstract: The invention relates to a console (13) for a sea unit (10), comprising: —a storage housing (27) delimiting an internal space for accommodating objects, and—a plate (31) movable between a closed position in which the movable plate (31) closes the opening (28) of the storage housing (27) and an open position in which the movable plate (31) is disengaged from the opening (28) of the storage housing (27) to allow access to the internal space of the storage housing (27), —the movable plate (31) extending in a horizontal plane in the closed position and in the open position (28), the movable plate (31) being capable of being retained in the horizontal plane while the movable plate (31) is being moved from the closed position to the open position and vice versa.
    Type: Application
    Filed: November 10, 2021
    Publication date: December 28, 2023
    Applicant: SAFRAN SEARTS
    Inventor: Bastien Bonnefoy
  • 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
  • CASTING RING FOR OBTAINING A PRODUCT MADE OF TITANIUM ALLOY OR A TITANIUM-ALUMINUM INTERMETALLIC ALLOY AND METHOD USING SAME
    Publication number: 20230415224
    Abstract: A casting ring having a first section made of a heat-conductive material and a second section made of a MAX phase alloy material, and a method for obtaining a product made of titanium alloy or a titanium-aluminum intermetallic compound by plasma torch melting, the alloy having an oriented structure, the method including heating the molten alloy surface in the casting ring with a plasma torch; cooling a cold zone of the casting ring over a length L1, the cooling forming a semi-solid crown of alloy; heating a hot zone of the casting ring over a length L2, thereby forming a solidification front, the flatness of which relative to a plane perpendicular to a drawing direction is less than 10°; and drawing the solidified alloy at a speed of more than 10?4 m/s in the drawing direction.
    Type: Application
    Filed: December 2, 2021
    Publication date: December 28, 2023
    Applicant: SAFRAN
    Inventor: Pierre Jean SALLOT
  • AIR INLET OF A TURBOMACHINE NACELLE INCLUDING A CIRCULATION CONDUIT OF A HOT AIR FLOW BETWEEN A MOVABLE UPSTREAM PART AND A FIXED DOWNSTREAM PART
    Publication number: 20230417182
    Abstract: Disclosed is an air intake of a turbine engine nacelle extending along an axis in which a flow of air circulates from upstream to downstream, the air intake extending annularly about the axis, the air intake having a movable upstream portion and a stationary downstream portion, at least one controllable movement member for moving the movable upstream portion between a retracted position and an extended position in order to enable circulation of an air flow passing between the movable upstream portion and the stationary downstream portion, at least one de-icing circuit having at least one circulation channel fluidically connecting the movable upstream portion and a hot air source, the circulation channel having at least one non-telescopic upstream pipe and at least one telescopic downstream member.
    Type: Application
    Filed: October 1, 2021
    Publication date: December 28, 2023
    Applicant: SAFRAN NACELLES
    Inventors: Hazem Kioua, Pierre Charles Caruel, Jean-Philippe Joret, Charles-Antoine Lampaert
  • DEVICE FOR CONTROLLING AN AIRFLOW GUIDING SYSTEM, IN PARTICULAR IN AN AIRCRAFT TURBINE ENGINE
    Publication number: 20230417156
    Abstract: Device (30) for controlling an airflow guiding system (20), comprising at least one actuator (31) configured to translate a control rod (32) between a first and a second end position of a nominal operating range in which at least one vane (21a) of the airflow guiding system (20) can be moved between a first and a second angle, the control rod (32) being connected to the vane (21a) by a control lever (33) comprising a first control rod (36) and a second control rod (37) which are hinged together. The actuator (31) is configured to bring the control rod (32) into a safety position located beyond the second end position of the nominal operating range and to orient the vane (21a) at a safe pitch angle between the first angle and the second angle.
    Type: Application
    Filed: November 10, 2021
    Publication date: December 28, 2023
    Applicant: SAFRAN HELICOPTER ENGINES
    Inventors: Frédéric Anthony Alain Imbourg, Pierre Chabanne, Thibaut Maxime Javoy
  • Method for quickly stopping the rotor of a helicopter after landing
    Patent number: 11852023
    Abstract: A method for quickly stopping the propulsion rotor of a helicopter after landing, comprising, following a request for quickly stopping the engine by a helicopter pilot, the following steps managed by the control unit of the turbomachine: Detecting the absence of the thermal stabilization phase of the gas generator of at least one turbomachine, controlling an extinction of the combustion chamber of the gas generator of at least one turbomachine, maintaining the rotation of the gas generator of which the combustion chamber is extinguished by means of said at least one electrical machine to ventilate the gas generator and stopping the main rotor of the helicopter by means of a mechanical brake.
    Type: Grant
    Filed: October 14, 2020
    Date of Patent: December 26, 2023
    Assignee: SAFRAN HELICOPTER ENGINES
    Inventors: Olivier Bedrine, Jean Michel Frédéric Louis Bazet, David Cazaux
  • 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 comprising a means of suspension
    Patent number: 11851201
    Abstract: The invention relates to a turbomachine (1) extending along an axis (X), comprising a high-pressure body with a high-pressure compressor (4) coupled in rotation to a high-pressure turbine (6), and a low-pressure body including a low-pressure compressor (3) coupled in rotation to a low-pressure turbine (7), an upstream casing (14) located upstream of the high-pressure compressor (4), and means of suspension (12, 13) for the turbomachine (1), intended for attaching the turbomachine (1) to an aircraft pylon (11).
    Type: Grant
    Filed: October 4, 2019
    Date of Patent: December 26, 2023
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Quentin Matthias Emmanuel Garnaud, Guillaume Glemarec, Hervé Jean Albert Mouton, Guilhem Seize, Benoit Bernard René Leclerc
  • 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
  • Mini suite emergency egress solutions
    Patent number: 11851186
    Abstract: Passenger seats having improved comfort emergency egress solutions for mini suites or other types of passenger seats that have a privacy screen, wall, or sliding door that divides the passenger seat from the aisle area or other common area. Specific embodiments find particular use on-board passenger transportation vehicles, such as aircraft, where comfort and privacy must be balanced with safety and federal regulations.
    Type: Grant
    Filed: January 27, 2023
    Date of Patent: December 26, 2023
    Assignees: Safran Seats USA LLC, Safran Seats
    Inventors: Bastien Bonnefoy, Arthur K. Glain, Victor Carlioz, Matthew Cleary, Eric O. Freienmuth, Patrick Herault, Christopher La Montagna
  • 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
  • Method and device for monitoring the hybridization of an aircraft
    Patent number: 11855549
    Abstract: Method for monitoring the distribution of power in a hybrid propulsion system comprising one or more electrical sources delivering an AC voltage, each of which is associated with an AC-to-DC controlled rectifier and one or more batteries, wherein, the AC-to-DC controlled rectifier and the battery each being connected directly to an HVDC bus supplying one or more electrical loads with power, the monitoring of the distribution of power is performed through the individual AC-to-DC controlled rectifier by a feedback loop to a power setpoint (Pref) on the basis of a measured power of the battery (Pbat) and a feedback loop to a voltage setpoint (Vref) on the basis of a measured voltage of the HVDC bus (VHVDC), either one of these two feedback loops delivering an RMS current setpoint Idref and Iqref for a feedback loop on the basis of a current (Igen) of the electrical source delivering an AC voltage.
    Type: Grant
    Filed: March 20, 2020
    Date of Patent: December 26, 2023
    Assignees: SAFRAN, SAFRAN ELECTRICAL & POWER, SAFRAN HELICOPTER ENGINES
    Inventors: Garance Vinson, Florent Rougier, Stéphane Meyer Beddok
  • Rotor blade for a turbomachine
    Patent number: 11852033
    Abstract: The invention relates to a rotor blade (10) for a turbomachine, in particular of an aircraft, comprising an airfoil (12) comprising a pressure face (15) and a suction face (17) extending from a leading edge (14) to a trailing edge (16), the airfoil (12) comprising an axis of elongation extending substantially along the leading (14) and trailing (16) edges, the airfoil (12) comprising a radially firmer end for connection to a rotor and a free radially outer end. According to the invention, the airfoil (10) further comprises at least one series of fins (24) situated on said free end, each of these fins (24) comprising a pressure face (26) situated on the suction face (17) side of the airfoil (12), and a suction face (28) situated on the pressure face (15) side of the airfoil (12).
    Type: Grant
    Filed: February 4, 2021
    Date of Patent: December 26, 2023
    Assignee: SAFRAN HELICOPTER ENGINES
    Inventors: Youssef Bouchia, Laurent Pierre Tarnowski
  • 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
  • DISCHARGE VALVE FOR AN AIRCRAFT AND ASSOCIATED METHOD
    Publication number: 20230406507
    Abstract: A discharge valve for an aircraft includes a cylindrical body having an inlet and an outlet, a first valve, and a second valve arranged inside the body. The first and the second valves are rotatable around a first axle and a second axle, respectively, between a closed position and an open position. A mechanism for locking the second valve in the closed position includes a control lever arranged around a third axle, an interface arranged on the second valve, and a device for rotating the third axle. The control lever is rotatably movable around the third axle between an unlocking position, in which the interface is in abutment against the drive device, and a locking position, in which the interface is engaged in the drive device.
    Type: Application
    Filed: October 15, 2021
    Publication date: December 21, 2023
    Applicant: SAFRAN AEROSYSTEMS FLUID
    Inventors: Denis SINDEZINGUE, David COSOLETO, Patrick BOURBON
  • METHOD FOR MANUFACTURING A TURBINE ENGINE VANE
    Publication number: 20230405668
    Abstract: A method for manufacturing a turbine engine vane a root connected to a blade extending in a longitudinal direction includes the steps of providing a root; and providing mold with a first cavity and a second cavity that together define a recess in which the vane is formed. The recess includes a first space in which the blade is formed and a second space in which the root (1), c) is formed. The method further includes the steps of providing aluminum strips; positioning a fibrous reinforcement; arranging the vane root in the second space; and injecting a foam comprising aluminum or injecting an aluminum alloy into the first space of the recess of the mold such that the foam impregnates the fibrous reinforcement.
    Type: Application
    Filed: October 25, 2021
    Publication date: December 21, 2023
    Applicants: SAFRAN, SAFRAN AERO BOOSTERS
    Inventors: Yann Jean-Pierre LEFAUX, Pierre Jean SALLOT
  • STATOR SUPPORT FOR A FAN SHAFT DRIVEN BY A REDUCTION GEARBOX IN A TURBOMACHINE
    Publication number: 20230407763
    Abstract: Stator structure (22) extending around an axis of the turbomachine and comprising: —a support (50) having an inner surface centred on the axis and —a flange (60) defining an air chamber (A2) and having an outer surface centred on the axis, the support (50) extending around the flange (60) such that the inner and outer surfaces are opposite to each other, the structure (22) defining an oil circuit and an air circuit which are formed by upstream channels (64, 65) and downstream channels (54, 55), —each upstream channel (64, 65) defining an outer opening in the outer surface, —each downstream channel (54, 55) defining an inner opening in the inner surface, each circuit being oriented between the outer and inner openings in a direction comprising a component radial to the axis.
    Type: Application
    Filed: September 24, 2021
    Publication date: December 21, 2023
    Applicant: Safran Aircraft Engines
    Inventors: Christophe Marcel Lucien PERDRIGEON, Didier Gabriel Bertrand DESOMBRE, Régis Eugène Henri SERVANT
  • ASSEMBLY FOR A TURBOMACHINE
    Publication number: 20230407813
    Abstract: An assembly for a turbomachine includes an exhaust cone and an exhaust casing having an annular inner shell. The exhaust cone and the exhaust casing can extend about a first axis, the exhaust cone can have an outer surface extending in the projection of the inner shell, the exhaust cone can be connected to the exhaust casing by means of a flange, the flange having an upstream portion fastened to the exhaust casing and lugs extending downstream from said upstream portion, and the exhaust cone can be fastened to the lugs. The flange can be sectorized and include of a plurality of angular sectors arranged so as to be circumferentially adjacent, with each flange sector having at least one lug extending rectilinearly along a second axis parallel to the first axis.
    Type: Application
    Filed: November 3, 2021
    Publication date: December 21, 2023
    Applicant: SAFRAN NACELLES
    Inventors: Jean-Philippe JORET, Vincent DEVANLAY, Fabien BRAVIN, Hélène MALOT