Patents Assigned to SAFRAN
  • AIRCRAFT LANDING GEAR
    Publication number: 20230076329
    Abstract: An aircraft landing gear comprising: a first member, a second member pivotally coupled to the first member, and a spring coupled to the first and second members, the spring comprising a plurality of elastically deformable washers, the spring being arranged to generate a biasing force between the first and second members to bias the first member toward a predetermined orientation relative to the second member.
    Type: Application
    Filed: February 4, 2021
    Publication date: March 9, 2023
    Applicant: SAFRAN LANDING SYSTEMS UK LTD
    Inventors: Pierre-Etienne Dandaleix, Thibault Hernandez, Andrew Mills
  • AIRCRAFT TURBOMACHINE CASING AND METHOD OF MANUFACTURING SAME
    Publication number: 20230075984
    Abstract: A casing of an aircraft turbomachine includes an annular shell extending around an axis A and made of a composite material having fibers that which are woven and embedded in a resin. An annular layer made of abradable material extends inside the shell, around axis A and is obtained by spreading and polymerizing a paste. Support panels extend around axis A and are interposed between the shell and the abradable layer.
    Type: Application
    Filed: January 26, 2021
    Publication date: March 9, 2023
    Applicants: SAFRAN AIRCRAFT ENGINES, SAFRAN AEROSPACE COMPOSITES
    Inventors: Meredith ROBERTS, Chris ANDERSON, Nicolas François Paul BROUSSAIS-COLELLA, Ambroise Nicolas Marie MALFROY, Foster Alexander MAXWELL, Paul MYSLINSKI, Adrienne RETIVEAU-LECA
  • AIRCRAFT LANDING GEAR ASSEMBLY
    Publication number: 20230071768
    Abstract: An aircraft landing gear assembly comprising: a structural pin defining a first bore having a longitudinal insertion axis; a cap for covering the bore, the cap comprising: a base portion; a head portion; a body portion positioned between the base portion and the head portion; and a bolt which extends between the head portion and the base portion and comprises a threaded portion so that engagement of either the head portion or the base portion with the threaded portion moves either the head portion or the base portion relative to the other, the body being formed of an elastically deformable material such that upon tightening of the bolt, the base portion moves towards the head portion and the elastically deformable material moves radially outwards such that a contact surface of the elastically deformable material engages with an inner surface of the first bore in order to retain the cap.
    Type: Application
    Filed: February 15, 2021
    Publication date: March 9, 2023
    Applicant: SAFRAN LANDING SYSTEMS UK LTD
    Inventors: Lee Williams, Doug Wight, Peter Millington, Steven Lawson
  • DATA TRANSMISSION METHOD AND ELECTRONIC CHIP OF THE MANYCORE TYPE
    Publication number: 20230075900
    Abstract: A method for transmitting data between functions implemented on a first electronic chip of the manycore type. The first electronic chip includes a plurality of execution cores, the execution cores being grouped in clusters, the clusters being interconnected by at least two communication systems. The data transmission method includes the steps of: implementing a first function on a first cluster; implementing a second function on a second cluster, characterised in that the second function is also implemented on a third cluster distinct from the first and second clusters; and transmitting at least one data item between the first function and the second function.
    Type: Application
    Filed: February 3, 2021
    Publication date: March 9, 2023
    Applicant: SAFRAN ELECTRONICS & DEFENSE
    Inventors: Louis-Théophile THIRION, Sangeerthman SUBRAMANIAM, Nicolas MAITROT, Jean-Charles RIAND
  • Method for balancing a set of blades
    Patent number: 11598212
    Abstract: A method for balancing a set of blades intended to be arranged on a bare disc of an aircraft engine, the bare disc comprising a defined number of numbered cells (ai) intended to receive the same defined number of blades, which can have a spread of mass, the method comprising the following steps:—sorting the blades by monotonic order of their mass (mi) to form an ordered set of blades,—separating the ordered set of blades in a balanced manner into four lobes constituted by a first large lobe, by a second large lobe, by a first small lobe and by a second small lobe, the blades being classified into each lobe according to a current placement order, and—arranging the four lobes on the bare disc by making the current placement order of the blades correspond to the numbered cells of the bare disc.
    Type: Grant
    Filed: October 25, 2018
    Date of Patent: March 7, 2023
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Antoine Victor Murry, Mourad Yahia Bacha, Jérôme Henri Noël Lacaille
  • Discharge door control ring for aircraft turbomachine and turbomachine comprising the same
    Patent number: 11598220
    Abstract: A control ring for controlling discharge gates for an aircraft turbine engine extends around a casing of the turbine engine and includes a connector for connecting to the gates. The control ring includes metal sectors and composite material sectors. The metal sectors may be connected to one another by the composite material sectors and the connector may be carried by the metal sectors.
    Type: Grant
    Filed: June 17, 2019
    Date of Patent: March 7, 2023
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Régis Eugène Henri Servant, Rémi Roland Robert Mercier
  • Architecture for a propulsion system of a helicopter including a hybrid turboshaft engine and a system for reactivating said hybrid turboshaft engine
    Patent number: 11597504
    Abstract: The present disclosure relates to an architecture of a propulsion system of a multi-engine helicopter comprising turboshaft engines connected to a power transmission gearbox, characterized in that it comprises: at least one hybrid turboshaft engine capable of operating in at least one standby mode during a stable cruise flight of the helicopter; at least two systems for controlling each hybrid turboshaft engine, each system comprising an electric machine connected to the hybrid turboshaft engine and suitable for rotating the gas generator thereof, and at least one source of electrical power for the electric machine, each reactivation system being configured such that it can drive the turboshaft engine in at least one operating mode among a plurality of predetermined modes.
    Type: Grant
    Filed: October 4, 2021
    Date of Patent: March 7, 2023
    Assignees: SAFRAN HELICOPTER ENGINES, SAFRAN ELECTRICAL & POWER
    Inventors: Philippe Vallart, Jean-Michel Bazet, Loic LeDuigou
  • Double-flow turbojet engine assembly with epicycloidal or planetary gearbox
    Patent number: 11598268
    Abstract: A turbojet engine including a shaft surrounded by a low-pressure rotor surrounded by a coaxial and independent high-pressure spool, this turbojet engine including from upstream to downstream: a fan driven by the shaft; a low-pressure compressor carried by the rotor; an inter-compressor casing; a high-pressure compressor and a high-pressure turbine carried by the high-pressure spool; an inter-turbine casing; a low-pressure turbine carried by the rotor; an exhaust casing; this turbojet engine including an upstream rotor bearing carried by the inter-compressor casing; a downstream rotor bearing carried by the exhaust casing; a gearbox downstream of the downstream bearing and through which the rotor drives the shaft; a downstream shaft bearing downstream of the downstream rotor bearing.
    Type: Grant
    Filed: November 21, 2019
    Date of Patent: March 7, 2023
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Guillaume Claude Robert Belmon, Cédric Zaccardi
  • Method for managing the energy of a system for verifying the inflation pressure of the tires of an aircraft
    Patent number: 11597244
    Abstract: Method for managing the energy in a system for verifying the inflation pressure of the tires of an aircraft, consisting in measuring, by a pressure sensor, at least one inflation pressure of each of the tires, obtaining a unique identification data relating to each of the tires, and sending via the wireless communication link the measurements and data thus collected to a processing unit disposed in or out of the aircraft for them to be available to a pilot or a maintenance operator, the step of sending the measurements and data being carried out in an acyclic manner as a function of a trigger signal given by a motion detector that detects the motion of the wheels of the aircraft as long as the speed is lower than a predetermined maximum speed.
    Type: Grant
    Filed: July 7, 2020
    Date of Patent: March 7, 2023
    Assignees: SAFRAN LANDING SYSTEMS, SAFRAN ELECTRONICS & DEFENSE
    Inventors: Olivier Dages, Didier Levavasseur, Stéphanie Nocente
  • Fan blade comprising a thin shield and a stiffener
    Patent number: 11598348
    Abstract: The invention relates to a fan blade (1) comprising: —an aerofoil (8) made of a composite material comprising a fibrous reinforcement densified by a polymer matrix, a leading edge (4) and a trailing edge (5), and —a structural shield (10) fitted and attached to the leading edge (4) or the training edge (5), and —at least one stiffener (20) formed integrally and in one piece with the structural shield (10), said stiffener (20) extending in a cavity (15) formed between the shield (10) and the leading edge (4) or the trailing edge (5) so as to increase a stiffness of the blade (1).
    Type: Grant
    Filed: December 13, 2019
    Date of Patent: March 7, 2023
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Thomas Alain De Gaillard, Benjamin Bulot, Eddy Keomorakott Souryavongsa
  • BLADE FOR A ROTATING BLADED DISK FOR AN AIRCRFT TURBINE ENGINE COMPRISING A SEALING LIP HAVING AN OPTIMIZED NON-CONSTANT CROSS SECTION
    Publication number: 20230068236
    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: Application
    Filed: February 11, 2021
    Publication date: March 2, 2023
    Applicant: 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
  • THRUST REVERSER COMPRISING DOORS FORMING AN UPWARD AIR DEFLECTION OPENING IN THE OPEN POSITION
    Publication number: 20230067232
    Abstract: A thrust reverser for an aircraft propulsion assembly, this reverser including a lower door and an upper door defining, in thrust reversal configuration, a deflection opening, through which a portion of the fluid not serving to produce the thrust reversal of the aircraft can exit the reverser downstream. The downstream edge of the lower door is offset towards the rear with respect to the downstream edge of the upper door so as to orient the fluid flow passing through the deflection opening vertically upwards. When the propulsion assembly is mounted at the rear portion of the fuselage of the aircraft, this makes it possible in particular to improve the supply of the control surface of the aircraft in the landing phase, in particular in crosswind conditions.
    Type: Application
    Filed: December 18, 2020
    Publication date: March 2, 2023
    Applicant: SAFRAN NACELLES
    Inventor: Sebastien Laurent Marie PASCAL
  • VARIABLE INDUCTIVE DISPLACEMENT SENSOR, ASSOCIATED DEVICE, SYSTEM AND AIRCRAFT
    Publication number: 20230068680
    Abstract: A variable inductive displacement sensor includes a primary excitation coil, a first secondary coil. and a second secondary coil. The primary excitation coil is configured to generate a variable magnetic field, and the first and second secondary coils are configured to each generate a signal induced by the variable magnetic field. The primary coil and the first and second secondary coils each have one end which is intended to be connected to a common ground.
    Type: Application
    Filed: August 31, 2022
    Publication date: March 2, 2023
    Applicant: SAFRAN ELECTRONICS & DEFENSE
    Inventor: Mathieu CONQ
  • FUEL SUPPLY CIRCUIT OF AN AIRCRAFT ENGINE
    Publication number: 20230064430
    Abstract: A fuel supply circuit of an aircraft engine includes a centrifugal pump mechanically coupled with an engine shaft delivering mechanical power. The circuit further includes at least one electromagnetic pump including at least one stator delimiting an annular internal volume in which is present a rotor able to drive a fluid, a plurality of magnets annularly distributed on the rotor and at least a plurality of coils annularly distributed inside the stator face-to-face with the magnets. The rotor is connected to the engine shaft by a one-way clutching element.
    Type: Application
    Filed: January 15, 2021
    Publication date: March 2, 2023
    Applicant: SAFRAN HELICOPTER ENGINES
    Inventors: Franck Albert Robert DUPEU, Jean-Marie André Robert GIGON, David Simon Serge TAIEB
  • METHOD FOR THE SURFACE TREATMENT OF ALUMINIUM-BASED PARTS
    Publication number: 20230064264
    Abstract: A method for the surface treatment of a part made of aluminum or aluminum alloy, comprising an anodization step and a step of sealing with a silicate salt. Additionally, a surface treatment method according to the invention for manufacturing an aluminium or aluminium alloy part intended, in particular for use in the aviation sector.
    Type: Application
    Filed: January 21, 2021
    Publication date: March 2, 2023
    Applicant: SAFRAN AEROSYSTEMS
    Inventors: Jean-Arthur DREVET, Valentin DESPREZ
  • METHOD FOR COMMUNICATION ACCORDING TO A TDMA PROTOCOL BETWEEN A MASTER DEVICE AND AT LEAST ONE SLAVE DEVICE
    Publication number: 20230060643
    Abstract: Disclosed is a method for communication, according to a TDMA protocol, between a master device and at least one slave device, during which a plurality of frames are transmitted between the master device and the slave device, each frame being partitioned into a plurality of time intervals, at least one time interval having an analogue synchronization signal having an amplitude regulation portion in the form of a sine wave having a constant amplitude over a number of predetermined pulses, and an optimized synchronization portion in the form of a triangular amplitude modulation of the sine wave so as to determine a reference time.
    Type: Application
    Filed: March 15, 2021
    Publication date: March 2, 2023
    Applicant: SAFRAN
    Inventors: Patrick Thomas, Raouia Ghodhbane
  • Mechanical gearbox for aircraft turbomachine
    Patent number: 11591972
    Abstract: A mechanical gearbox for an aircraft turbomachine includes a sun gear having an axis (X) of rotation, a ring gear around the sun gear, and planet gears meshed with the sun gear and the ring gear. Each planet gear has a first toothing meshed with the sun gear and a second loathing meshed with the ring gear. The first toothing includes a series of upstream teeth and a series of downstream teeth located on either side of a plane (H) perpendicular to the axis (X) of rotation of the sun gear. The second toothing includes a series of upstream teeth and a series of downstream teeth located on either side of the plane (H) and separated from one another by the first toothing, these teeth being parallel to one another and to the axis (Y) of rotation of the planet gear.
    Type: Grant
    Filed: June 11, 2021
    Date of Patent: February 28, 2023
    Assignee: SAFRAN TRANSMISSION SYSTEMS
    Inventors: Guillaume Julien Beck, Dhafer Ghribi, Simon Loïc Clément Lefebvre, Quentin Pierre Henri Pigott, Adrien Louis Simon
  • Air intake of an aircraft turbojet engine nacelle comprising ventilation orifices for a de-icing flow of hot air
    Patent number: 11591960
    Abstract: The invention relates to an air intake of an aircraft turbojet engine nacelle, extending along an axis X, in which an air flow circulates from upstream to downstream, the air intake extending circumferentially around the axis X and comprising an inner wall, which faces the axis X in order to guide an inner air flow, and an outer wall, which is opposite the inner wall, for guiding an external air flow, the walls being connected by a leading edge and an inner partition so as to delimit an annular cavity. The air intake comprises means for injecting at least one hot air flow into the inner cavity and at least one ventilation orifice formed in the outer wall in order to allow the hot air flow to escape after heating the internal cavity, the air intake comprising at least one disruption member of the external air flow, positioned upstream of the ventilation orifice, which extends outwardly from the outer wall.
    Type: Grant
    Filed: January 22, 2020
    Date of Patent: February 28, 2023
    Assignee: SAFRAN NACELLES
    Inventors: Sébastien Laurent Marie Pascal, Jean-Michel Paul Ernest Nogues, Marc Versaevel, François Chauveau
  • Method of fabricating an electronic power module by additive manufacturing, and associated substrate and module
    Patent number: 11594475
    Abstract: A method of fabricating an electronic power module by additive manufacturing, the electronic module including a substrate having an electrically insulating plate presenting opposite first and second faces, with a first metal layer arranged directly on the first face of the insulating plate, and a second metal layer arranged directly on the second face of the insulating plate. At least one of the metal layers is made by a step of depositing a thin layer of copper and a step of annealing the metal layer, and the method further includes a step of forming at least one thermomechanical transition layer on at least one of the first and second metal layers, the at least one thermomechanical transition layer including a material presenting a coefficient of thermal expansion that is less than that of the metal of the metal layer.
    Type: Grant
    Filed: September 15, 2021
    Date of Patent: February 28, 2023
    Assignee: SAFRAN
    Inventors: Rabih Khazaka, Stéphane Azzopardi, Donatien Henri Edouard Martineau
  • Assembly for a turbomachine turbine
    Patent number: 11591924
    Abstract: An assembly for a turbomachine turbine includes a housing (1) extending circumferentially about an axis X, sectors (2) intended to form a ring capable of delimiting a gas flow path, each sector (2) comprising a first side (17) and a second side (18) extending radially and circumferentially about the said axis X and spaced axially from each other, each side (17, 18) of the sector (2) including at least one radial bearing surface of an oblong hole capable of cooperating with support pins (13, 14) of the housing (1), at least one of the sides (17, 18) including means (23) for the circumferential positioning of the sector (2) with respect to the housing (1), wherein each radial bearing surface is cylindrical relative to axis X and is capable of bearing on a complementary cylindrical surface relative to axis X of a support pin.
    Type: Grant
    Filed: February 26, 2020
    Date of Patent: February 28, 2023
    Assignee: SAFRAN CERAMICS
    Inventors: Christophe Paul Aupetit, Thierry Guy Xavier Tesson, Clément Marie Benoît Roussille, Cécile Marie Emilienne Chevalier