Patents Assigned to SAFRAN
  • BLADE COMPRISING A COMPOSITE MATERIAL STRUCTURE AND ASSOCIATED MANUFACTURING METHOD
    Publication number: 20230044779
    Abstract: The present invention relates to a blade (7) comprising: —a composite material structure (17), —a blade root fastening portion (9) further comprising a shoulder (10) extending into the recess from the wall—a base (18) arranged in the recess and comprising a support member configured to abut against the shoulder (10) of the blade root fastening portion (9) and a passage (39) formed in the support member, the sections (23) of the blade root portion (22) of the composite material structure extending through the passage (39), and—a blocking part (19) arranged in the recess between the two sections (23) of the blade root portion (22) such that each section of the blade root portion (23) is pressed against the support member by the blocking part (19).
    Type: Application
    Filed: January 19, 2021
    Publication date: February 9, 2023
    Applicant: Safran Aircraft Engines
    Inventors: Vincent JOUDON, Vivien Mickaël COURTIER, Clément Pierre POSTEC
  • CONTROL METHOD AND UNIT FOR CONTROLLING THE CLEARANCE OF A HIGH-PRESSURE TURBINE TO REDUCE THE EFFECT OF EGT OVERSHOOT
    Publication number: 20230044006
    Abstract: Method for controlling a clearance between the tips of the blades of a rotor of an aircraft engine turbine and a turbine ring, comprising the estimation of the clearance to be controlled and the control of a valve delivering an air stream directed towards the turbine ring based on the thus estimated clearance, this method comprising: the detection of a transient acceleration phase based on at least one parameter representative of the engine; the receipt of a data relating to the altitude of the aircraft; the determination of data representative of the temperature of the rotor during the transient acceleration phase and in steady speed and the calculation of a relative temperature deviation.
    Type: Application
    Filed: January 4, 2021
    Publication date: February 9, 2023
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Jérôme Claude George LEMONNIER, Damien BONNEAU, Cécile RACINET, Antoine Bruno VAN NOORT
  • THRUST REVERSER COMPRISING DOORS AND AT LEAST ONE RETRACTABLE DEFLECTOR FOR CLOSING A LATERAL OPENING
    Publication number: 20230039569
    Abstract: A thrust reverser including doors and at least one flexible deflector obstructing a lateral opening of the thrust reverser when the doors are open. Such a deflector allows better controlling the airflows in thrust reverser configuration and maximizing the counter-thrust force.
    Type: Application
    Filed: December 18, 2020
    Publication date: February 9, 2023
    Applicant: SAFRAN NACELLES
    Inventors: Sebastien Laurent Marie PASCAL, Patrick GONIDEC, Alexandre PHI, Paul FERREY
  • MEASURING THE PRESSURE IN THE EXPANSION CHAMBER OF AN ENCAPSULATED SHOCK ABSORBER IN AN AIRCRAFT LANDING GEAR
    Publication number: 20230038683
    Abstract: An encapsulated shock absorber of an aircraft undercarriage includes a sliding rod slidably mounted in a leg strut of the undercarriage and an inner cylinder extending inside the strut. The inner cylinder is fastened to the strut via a top end, and the rod slides around the inner cylinder. The inner cylinder is terminated inside the sliding rod by a diaphragm that defines an oil chamber in the shock absorber and inside the sliding rod. A mixed oil/gas chamber is located in the inner cylinder, and an expansion chamber extends between the sliding rod and the inner cylinder. A hole being made in the inner cylinder in register with the expansion chamber is connected by a pipe to a pressure sensor situated outside the strut. The pipe extends inside the inner cylinder from the hole to the top end of the inner cylinder.
    Type: Application
    Filed: February 26, 2021
    Publication date: February 9, 2023
    Applicant: SAFRAN LANDING SYSTEMS
    Inventors: Philippe HENRION, Arnaud LAFITTE
  • Turbomachine for aircraft comprising a plurality of variable bypass valves and control method
    Patent number: 11572839
    Abstract: A turbomachine for an aircraft extending axially along an axis X comprising a primary flow path in which an air stream flows intended for the combustion chamber and a secondary flow path in which an air stream flows intended for propulsion, the compressor comprising a plurality of first variable bypass valves, a plurality of second variable bypass valves, the turbomachine comprising a first control system configured to control the movement of the plurality of first variable bypass valves and a second control system configured to control the movement of the plurality of second variable bypass valves, the first control system and the second control system being separate.
    Type: Grant
    Filed: July 2, 2019
    Date of Patent: February 7, 2023
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Mathieu Daniel Marie Van Gansen, Lise Jeanne Bernadette Guillot
  • Aircraft engine nacelle with asymmetric fan cowls
    Patent number: 11572188
    Abstract: A nacelle for an aircraft engine comprising a first fan cowl and a second fan cowl, each fan cowl comprising a hinged end and a closing end, each fan cowl being mobile between a closed operating position and an open maintenance position, the first fan cowl having a larger angular coverage than the second fan cowl, the first fan cowl comprising an upper part connected to a lower part by an intermediate hinge so as to allow the lower part to fold towards the upper part.
    Type: Grant
    Filed: August 20, 2021
    Date of Patent: February 7, 2023
    Assignee: SAFRAN NACELLES
    Inventors: Ophélie Schmitter, Hazem Kioua, Romain Gardel, Damien Lemoine
  • Blade pivot of adjustable orientation and of reduced bulk for a turbomachine fan hub
    Patent number: 11572889
    Abstract: A blade pivot of adjustable orientation for a turbomachine fan hub includes: a block having a retaining device configured to retain a fan blade root and a coupling device for the transmission of a torque; a ball type rolling bearing for taking up centrifugal forces having an inner ring; a clamping nut screwed onto an external thread of the block in order to clamp the inner ring of the ball type rolling bearing for taking up centrifugal forces to the block; a rolling bearing for taking up transverse forces; a pitch setting transmission ring positioned inside the inner radial end of the block and equipped with a coupling device cooperating with the coupling device of the block, and a device for locking the pitch setting transmission ring on the block.
    Type: Grant
    Filed: January 31, 2020
    Date of Patent: February 7, 2023
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Vincent François Georges Millier, Caroline Marie Frantz, Gilles Alain Marie Charier, Olivier Belmonte
  • Valve of a hydraulic circuit with constant pressure drop
    Patent number: 11572960
    Abstract: A pressure valve including a body including at least one admission opening and at least one discharge opening, a slide valve sliding in the body, the slide valve defining a chamber, with the body, and including a head arranged facing a seat of the admission opening, a spring pressing the head of the slide valve against the seat, a lip for applying the head to the seat. The head includes at least one hole bringing the chamber into communication with the discharge opening, each hole being arranged facing the seat and downstream from the lip in relation to the admission opening in order to reduce the pressure in the chamber by a Venturi effect when the slide valve is open.
    Type: Grant
    Filed: December 3, 2018
    Date of Patent: February 7, 2023
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Lancelot Guillou, Stéphane Louis Lucien Auberger
  • Method for preparing a support and for acoustic management on a turbine engine or a nacelle
    Patent number: 11572832
    Abstract: The invention relates to acoustic management, on an aircraft turbomachine (3,12) or on a nacelle (1,10), via a panel (30,32). On a support (38) is reserved a recess (34), recessed with respect to a surrounding general surface (36) for contact with moving air. The recess (34) is adapted to receive the panel, as another so-called surface for contact with moving air. The support (38) and/or the panel comprise removable connecting elements for, in the recess (34), mounting it removably with respect to the support, the panel being an acoustic panel or a non-acoustic panel.
    Type: Grant
    Filed: September 20, 2019
    Date of Patent: February 7, 2023
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Norman Bruno André Jodet, Jean-Michel Daniel Paul Boiteux, Francis Couillard, Jérémy Paul Francisco Gonzalez, Stéphane Orcel
  • Aircraft engine assembly with a supply path to an inter-flow compartment tank of turbine engine
    Patent number: 11572833
    Abstract: An aircraft engine assembly includes a dual-flow turbine engine, a pylon for mounting the turbine engine, thrust-absorbing rods connecting the turbine engine to the pylon, and an inter-flow compartment housing a lubricant tank. In order to facilitate the filling of the tank, a lubricant supply path is fluidly connected to the tank, this path passing through an inner hollow region of at least one of the two thrust-absorbing rods.
    Type: Grant
    Filed: April 2, 2019
    Date of Patent: February 7, 2023
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Antoine Elie Hellegouarch, Frédéric Paul Eichstadt, Quentin Matthias Emmanuel Garnaud
  • TURBINE OVERSPEED DISENGAGEMENT DEVICE FOR A TURBINE ENGINE
    Publication number: 20230033362
    Abstract: An assembly for a turbine engine turbine includes a turbine rotor disc centered on a longitudinal axis, a turbine shaft centered on the longitudinal axis and driven in rotation by the rotor disc. The assembly further includes first means of transmitting torque from the rotor disc to the shaft, wherein the rotor disc is locked in translation relative to the shaft in the direction of the longitudinal axis by a screwed member on the said shaft and second means of transmitting torque from the rotor disc to the screwed member. The screwed member has an unscrewing direction identical to the direction of rotation of the rotor disc in operation, and the second means of transmitting torque are configured to transmit the rotational torque from the rotor disc to the screwed member when the first means of transmitting torque cease to transmit torque from the rotor disc to the shaft.
    Type: Application
    Filed: January 8, 2021
    Publication date: February 2, 2023
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Antoine Hervé DOS SANTOS, Joao Antonio AMORIM, Pascal Grégory CASALIGGI, Nicolas Xavier TRAPPIER
  • LOCATING A TRANSMITTER BY MEANS OF A PLURALITY OF GEOGRAPHICALLY REMOTE RECEIVING STATIONS USING KNOWN OBJECT PATHS
    Publication number: 20230037150
    Abstract: The invention relates to a method for locating a transmitter, which is implemented in a processing unit of a processing station of a locating system.
    Type: Application
    Filed: December 24, 2020
    Publication date: February 2, 2023
    Applicant: SAFRAN DATA SYSTEMS
    Inventors: Baptiste GUILLOT, Yann PICARD
  • CAPTURE PIN FOR A LOCKING HOOK
    Publication number: 20230031765
    Abstract: An aircraft landing gear includes a landing gear provided with a yoke supporting a spindle on which is mounted a capture pin to be hooked by a hook of a locking box to be mounted on a structure of an aircraft to immobilize the landing gear in a given position with respect to the structure. The capture pin includes a body provided with a longitudinal opening enabling the capture pin to be mounted on the spindle, and an outer surface of revolution having a central portion having a convex profile to cooperate with the hook. A central portion of the outer surface is formed on a central ring which is mounted so as to rotate freely on a central portion of the body.
    Type: Application
    Filed: January 8, 2021
    Publication date: February 2, 2023
    Applicant: SAFRAN LANDING SYSTEMS
    Inventor: Ludovic DUFAY
  • ELECTROTECHNICAL DEVICE FOR AN AIRCRAFT
    Publication number: 20230033439
    Abstract: An electrotechnical device for an aircraft includes a housing having a surface and a magnetic circuit formed by a stack of laminated sheets and composed of a yoke. The yoke is fixed on the surface of the housing by means of a thermal interface and has a surface. At least one low-frequency coil component is attached to at least part of the surface of the yoke by attachment means.
    Type: Application
    Filed: December 11, 2020
    Publication date: February 2, 2023
    Applicant: SAFRAN ELECTRICAL & POWER
    Inventors: Nicolas BERNARD, Sonia DHOKKAR
  • SUPERCONDUCTING BULK COMPRISING A CAVITY AND ASSOCIATED ELECTRIC MACHINE
    Publication number: 20230037086
    Abstract: The present invention relates to a superconducting pellet for a superconducting electrical machine, the superconducting pellet having a circumferential wall, the circumferential wall having: a first border, a second border opposite the first border, an inner face connecting the first border to the second border, an outer face opposite the inner face, and a cavity formed between the first border and the second border and defined by the inner face, and an additional wall which covers the first border or is flush with the first border so as to at least partially cover the cavity, or extends from the inner face at a distance from the first border and the second border so as to divide the cavity into two portions.
    Type: Application
    Filed: December 7, 2020
    Publication date: February 2, 2023
    Applicants: SAFRAN, UNIVERSITE DE LORRAINE
    Inventors: Sabrina Siham AYAT, Alexandre COLLE, Rémy BIAUJAUD
  • COMPOSITE BLADE FOR AN AIRCRAFT ENGINE AND METHODS FOR MANUFACTURING AND REPAIRING SAME
    Publication number: 20230036890
    Abstract: A process for manufacturing a blade made of composite material for a turbomachine. The blade includes an airfoil having a pressure side and a suction side which extend from a leading edge to a trailing edge of the airfoil. The blade further includes a metal sheath that extends along the leading edge of the airfoil. The process includes the steps of: placing a preform, produced by three-dimensionally weaving fibers, in a mold, the sheath being positioned on an edge of the preform intended to form the leading edge of the airfoil; and injecting polymerizable resin into the mold to impregnate the preform so as to form the airfoil after solidifying. At least one double-sided adhesive film may be inserted between the sheath and the edge of the preform prior to injection of the resin.
    Type: Application
    Filed: November 23, 2020
    Publication date: February 2, 2023
    Applicant: SAFRAN
    Inventors: Adrien Touze, Nicolas Pierre Lanfant, Romain Picon, Loïc Sorgnard
  • METHOD FOR MONITORING AN ENGINE CONTROL UNIT
    Publication number: 20230036687
    Abstract: Methods are provided for supervising a motor control unit with at least two separate channels, each of the two channels including at least: means for executing a given application task AS, the application task AS including a plurality of successively executed computations between which latency periods elapse; a first component capable of performing the computations; a second component capable of storing data; the application tasks AS of the channels being capable of communicating. The method comprising includes the following steps: a) detecting a latency period; b) performing, during this latency period, an operating state test of at least one of the components; and c) determining a state of the component corresponding to a failure state or a healthy state.
    Type: Application
    Filed: April 30, 2020
    Publication date: February 2, 2023
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventor: Christophe Pierre Georges Martin
  • Internal turbomachine casing having improved thermal insulation
    Patent number: 11566538
    Abstract: An internal casing ferrule for a turbomachine, centered on a longitudinal central axis, which includes: a main body centered on this axis, with two ends, delimited by surfaces that are radially inner and outer relative to this axis; a thermal porous-structure insulation envelope having a volumetric porosity ?50%, which includes: a lateral portion entirely covering the two ends; when viewed in section transversely to this axis, exterior and interior portions entirely covering, respectively, the radially outer and inner surfaces of the main body; and a protective envelope which at least partially covers the envelope and which includes, when viewed in section transversely to this axis, radially outer and inner protective portions, respectively covering, at least in part, the exterior and interior portions.
    Type: Grant
    Filed: September 17, 2019
    Date of Patent: January 31, 2023
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventor: Christophe Scholtes
  • Aircraft wheel braking system, configurable to occupy a normal mode or an RTO mode
    Patent number: 11565670
    Abstract: An electric braking system (1) for braking an aircraft, the system comprising: a brake (3) comprising an electromechanical actuator (5) designed so that when it applies a force to the friction members (4) that is less than or equal to a first maximum threshold, no degradation of the actuator occurs, and when it applies a force to the friction members (4) that is greater than the first maximum threshold, degradation is likely to occur; control means (7) configurable to occupy a first mode in which the controlled braking force cannot exceed the first maximum threshold, and to occupy a second mode in which the controlled braking force can reach the second maximum threshold; and configuration means (10) arranged to configure the control means (7) to occupy the second mode when in a situation preceding a potential interruption of takeoff (RTO) of the aircraft, and otherwise to occupy the first mode.
    Type: Grant
    Filed: April 1, 2020
    Date of Patent: January 31, 2023
    Assignee: SAFRAN LANDING SYSTEMS
    Inventors: Nathanaël Richard, Romain Presle
  • Turbomachine ring
    Patent number: 11566540
    Abstract: Turbomachine ring as well as a turbomachine comprising such a ring and a method for repairing such a ring, the turbomachine ring comprising an essentially cylindrical support, including a frontal surface wherein a notch is formed, one or more sectors forming an annulus configured to embody a segment of air stream, each sector comprising a hook portion protruding in the direction of the support and engaging in the notch of the support, and an anti-wear device having a U shaped portion, provided in the notch of the support and pressed at least against the radially external surface of the notch, and a tab portion, continuously extending the U shaped portion, pressed and fastened against the frontal surface of the support.
    Type: Grant
    Filed: January 9, 2019
    Date of Patent: January 31, 2023
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Quentin Pierre Hubert Bomberault, Martin Jubien, Julien Michel Auguste Robert