Patents Assigned to SAFRAN
  • Publication number: 20220307446
    Abstract: A thrust reverser for an aircraft propulsion assembly, this reverser including an outer structure movable between a closed position and an open position of two primary latches configured to lock the movable outer structure in the closed position. The movable outer structure includes an output end that is oblique with respect to the longitudinal central axis so as to orient the thrust laterally. In order to compensate the tilting moment of the movable outer structure, which results from this lateral orientation of the thrust, the primary latches are offset with respect to a median longitudinal plane passing through the longitudinal central axis of the reverser.
    Type: Application
    Filed: September 2, 2020
    Publication date: September 29, 2022
    Applicant: SAFRAN NACELLES
    Inventors: Pierre Charles CARUEL, Fabien CHARLIAC, Fabien BRAVIN, Loïc CHAPELAIN
  • Publication number: 20220305582
    Abstract: A tooling holds a blade during friction welding to a rotor element. The tooling includes a fixed jaw having a central part; two arms separated by a distance d for receiving at least one portion of the blade; and a fixed jaw body with bearing surfaces and a bore for receiving at least one portion of the blade. The bearing surfaces are configured to come into contact with the blade. A movable jaw includes a movable bearing surface that comes into contact with the blade, and pressure means that moves the movable jaw towards the fixed jaw body to press the blade.
    Type: Application
    Filed: September 3, 2020
    Publication date: September 29, 2022
    Applicant: SAFRAN AERO BOOSTERS
    Inventor: Bruno Henri Marcel VREULS
  • Publication number: 20220306168
    Abstract: A disclosed controller is configured with logic that, when executed, performs actions to extend landing gear of a maglev vehicle. The actions include receiving a height control target value and transitioning between a standby control state and an active control state. The controller maintains the landing gear in a fixed position when the controller is in the standby control state, and the controller controls extension and retraction of the landing gear according to the height control target value when the controller is in the active control state.
    Type: Application
    Filed: March 29, 2021
    Publication date: September 29, 2022
    Applicants: SAFRAN LANDING SYSTEMS CANADA INC., SAFRAN LANDING SYSTEMS
    Inventors: Andrew Michael Ellis, Graeme Peter Arthur Klim, Thibaud Mazoue
  • Patent number: 11454136
    Abstract: The invention relates to a method for producing a shielding cartridge (1) of a turbomachine element (10), said method comprising a step of winding a carbon wire (3) comprising a plurality of fibres about a longitudinal axis and a step of trapping and preserving the outside surroundings of the wound-up wire (3) in a housing (2).
    Type: Grant
    Filed: December 11, 2017
    Date of Patent: September 27, 2022
    Assignee: SAFRAN HELICOPTER ENGINES
    Inventor: Ludovic Meziere
  • Patent number: 11452889
    Abstract: Oxygen-delivery systems are described. The systems may supply emergency respiratory gas on demand to aircraft passengers. To reduce risk of blockage of tubes delivering anti-blocking gas to the face masks worn by the passengers, the systems may be designed to provide a continuous trickle flow of respiratory gas, or one or more anti-blocking pulses of gas, into a delivery tube.
    Type: Grant
    Filed: January 22, 2019
    Date of Patent: September 27, 2022
    Assignee: SAFRAN AEROTECHNICS SAS
    Inventors: Stuart David Dixon Walker, Vincent Gérard Greter
  • Patent number: 11454117
    Abstract: A rotor for a contrarotating turbine comprising a drum and a blading mounted inside, the drum comprising a hook delimiting a housing having an outer wall and an inner wall, the blading comprising a blade and an outer platform provided with spoiler placed inside the housing, wherein the rotor comprises a foil comprising an elastic inner wing and an outer wing, the outer wing being arranged radially between the spoiler and the outer wall, the inner wing having a first support with the inner wall and a second support with the spoiler, the inner wing being arranged in the housing so as to exert a force on the spoiler so as to press the spoiler against the outer wall via the outer wing.
    Type: Grant
    Filed: March 6, 2020
    Date of Patent: September 27, 2022
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Patrick Jean Laurent Sultana, Olivier Renon, Laurent Cédric Zamai, Clément Charles Jérémy Coiffier
  • Patent number: 11456693
    Abstract: A smart motor having a permanent magnet synchronous machine and an electronic control unit, the synchronous machine including one or two permanent magnet rotor(s) and at least one six-phase stator per rotor endowed with at least two three-phase assemblies each formed of three windings electrically coupled in a star, the electronic control unit including one control inverter per stator equipped with six independent arms each configured to control one phase of a six-phase stator. The three-phase assemblies are magnetically and electrically decoupled with respect to one another.
    Type: Grant
    Filed: December 2, 2019
    Date of Patent: September 27, 2022
    Assignee: SAFRAN ELETRICAL & POWER
    Inventors: Olivier Berry, José Soler, Jérémy Cuenot, Sonia Dhokkar
  • Patent number: 11453501
    Abstract: An arrangement of individual seats intended to be installed in a cabin of an aeroplane includes at least one assembly of two seats turned towards the interior in the direction of the longitudinal axis of the arrangement. An end assembly includes a first seat and a second seat, each seat being convertible between a sitting position and a recumbent position in which the seat defines a bed surface. An intermediate element includes a surface, referred to as the intermediate surface, located in the same plane as the bed surfaces of the first seat and of the second seat, such that the bed surfaces of the first seat and of the second seat as well as the intermediate surface form a common bed surface.
    Type: Grant
    Filed: March 29, 2018
    Date of Patent: September 27, 2022
    Assignee: Safran Seats
    Inventors: Jeremy White, Nicholas Sandham, Richard Seale, Omar Chraibi
  • Patent number: 11454194
    Abstract: A nacelle for a bypass turbojet engine includes a cascade thrust reverser provided with reversal cascades arranged around an annular stream of fresh air, beneath front cowls. The cascades move backward with movable rear cowls, opening side passages in the annular stream, which receive the cascades for directing the fresh air flow forward, the bypass turbojet engine. The bypass turbojet engine includes fixing points, and the nacelle includes outer hatches closing openings of the front cowls, which are arranged radially outside the fixing points for access thereto, each hatch opening including a contour with edges of two front cowls.
    Type: Grant
    Filed: June 22, 2020
    Date of Patent: September 27, 2022
    Assignee: Safran Nacelles
    Inventors: Patrick Boileau, Pierre Caruel
  • Patent number: 11454135
    Abstract: The invention concerns a device for centring and guiding in rotation a rotating part rotating about a turbomachine axis, comprising a rolling bearing comprising an outer ring, a bearing support surrounding the outer ring, an annular attachment flange mounted on the bearing support and a flexible portion connecting the outer ring to the attachment flange and comprising first arms extending from the attachment flange in a first direction with a first radial component towards the inside, second arms extending from the outer ring of the rolling bearing in a second direction with a second radial component opposite the first radial component, towards the outside, and an annular base that the first arms and the second arms join; the first arms alternating circumferentially with the second arms.
    Type: Grant
    Filed: November 14, 2019
    Date of Patent: September 27, 2022
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Régis Eugène Henri Servant, Didier Gabriel Bertrand Desombre
  • Publication number: 20220297189
    Abstract: Additive manufacturing equipment includes a laser head intended to emit a laser beam defining a longitudinal axis (X), a first, a second, and a third container respectively aligned in a first transverse plane substantially perpendicular to the longitudinal axis (X), the three containers each including a movable plate that can move along the longitudinal axis (X), each plate being intended to receive a thickness of powder of which the free ends define three powder beds aligned in a second transverse plane, the equipment additionally including a movable scraper intended to move in a third plane transverse with respect to the surface of the containers so as to be in contact with each of the powder beds. The equipment includes a first and a second movable shield that are intended to move in the same third transverse plane as the movable scraper.
    Type: Application
    Filed: August 26, 2020
    Publication date: September 22, 2022
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventor: Matthieu Vial
  • Publication number: 20220297818
    Abstract: An acoustic panel for an aircraft comprising: a sound attenuating sheet having a plurality of cavities, a sound attenuating sheet having a first surface, a second surface opposite to the first surface and an end surface connecting the first and second surfaces, a first sheet extending over at least a portion of the first surface and over the end surface, and a second sheet extending over the second surface and the end surface, wherein the first and the second sheets are connected such that a tensile force can be transferred therebetween.
    Type: Application
    Filed: May 7, 2020
    Publication date: September 22, 2022
    Applicant: Safran Nacelles Limited
    Inventors: Dave Kirk, Graeme Hill, Dave Hebden, Simon Furmston
  • Publication number: 20220297825
    Abstract: An aircraft comprising a fuselage, a pair of wings connected to an upper portion of the fuselage, and a pair of wing support struts, each wing support strut being connected between a lower portion of the fuselage and an underside of the adjacent wing, wherein at least one centre landing gear assembly is connected to the fuselage and is configured to be retractable within the fuselage, and a respective outrigger landing gear is connected to each wing support strut, each outrigger landing gear being configured to be retractable within the respective wing support strut.
    Type: Application
    Filed: April 15, 2020
    Publication date: September 22, 2022
    Applicant: SAFRAN LANDING SYSTEMS UK LTD
    Inventor: Yann Simonneaux
  • Publication number: 20220299040
    Abstract: A turbomachine assembly is provided. The assembly includes: a first rotor module including a first blade, a second rotor module, connected to the first rotor module, and including a second blade of smaller length than the first blade, and a damping device including a plurality of first radial external surfaces supported with friction against the first module. The damping device is stepped, and includes a second radial external surface supported with friction against the second module, so as to couple the modules for the purpose of damping their respective vibrational movements during operation.
    Type: Application
    Filed: December 17, 2018
    Publication date: September 22, 2022
    Applicant: Safran Aircraft Engines
    Inventors: Philippe Gerard Edmond JOLY, Marie-Oceane PARENT, Francois Jean COMIN, Romain Nicolas LAGARDE, Jean-Marc Claude PERROLLAZ, Laurent JABLONSKI, Charles Jean-Pierre DOUGUET
  • Publication number: 20220298990
    Abstract: An exterior nozzle member for a turbomachine extending along an axis oriented from upstream to downstream and comprising a primary duct configured to conduct a primary flow, an annular cavity of axis and a turbine, said exterior nozzle member comprising: an acoustic attenuation panel formed by an acoustic attenuation structure on which there are mounted an interior wall and an exterior wall facing the primary duct and the annular cavity, respectively, a nozzle flange connected to the panel and comprising an upstream end configured to be connected to a turbine casing flange and a sealing member connected to the panel and comprising an interior longitudinal branch extending radially inside the nozzle flange in order to thermally protect it from the primary flow, the nozzle flange being made of a first material and the sealing member being made of a second material, the first material having a coefficient of thermal expansion greater than that of the second material.
    Type: Application
    Filed: September 10, 2020
    Publication date: September 22, 2022
    Applicant: SAFRAN NACELLES
    Inventors: Olivier Chapelle, Dimitri Kostin, Clotaire Beauvais
  • Patent number: 11447109
    Abstract: A control method of an electrical braking system for aircraft includes a plurality of electromechanical actuators capable of applying a braking force on friction members. Each electromechanical actuator includes an electric motor equipped with one or more windings. The braking system further includes at least one power module configured to send to each electric motor winding a phase current and at least one control module configured to control, in response to a braking setpoint, the sending by the power module of a setpoint phase current determined depending on the braking force to be applied. The method further includes the variation of the phase current transmitted to each winding of the electric motor so as to cause the phase current to oscillate around the setpoint phase current.
    Type: Grant
    Filed: May 5, 2020
    Date of Patent: September 20, 2022
    Assignee: SAFRAN LANDING SYSTEMS
    Inventor: Olivier Frey
  • Patent number: 11448095
    Abstract: The invention relates to a tank (32) for liquid, in particular of a turbine engine such as an aircraft turbojet engine, the tank comprising an external wall (36) with an inner surface (48); an inner chamber intended for containing the liquid of the tank (32) and defined by the inner surface of the external wall; and a system (42) for measuring the level of liquid. The system comprises: a submersible portion matching the inner surface of the wall (36); a clearance (52) separating the submersible portion from the inner surface; and a liquid detector (54) configured to emit a signal towards the submersible portion through the clearance, said signal being configured to be modified in the event that liquid is present in the clearance (52). The invention likewise relates to a method for measuring a level of liquid, and an associated computer program.
    Type: Grant
    Filed: April 17, 2019
    Date of Patent: September 20, 2022
    Assignee: SAFRAN AERO BOOSTERS SA
    Inventor: Jean-François Cortequisse
  • Patent number: 11447157
    Abstract: A passive lateral stability system maintains the position of a vehicle relative to a guideway. The system includes first and second guide assemblies that urge the vehicle away from first and second electrically conductive guide walls, respectively. The first guide assembly includes a wheel configured to reciprocate toward and away from the first guide wall. A biasing element bias biases the wheel toward the first guide wall. The system further includes a magnetic element associated with the wheel, wherein movement of the magnetic element relative to the first guide wall produces a magnetic force that biases the wheel away from the first guide wall. A second guide assembly is mounted to the vehicle and urges the vehicle away from the second guide wall.
    Type: Grant
    Filed: May 6, 2020
    Date of Patent: September 20, 2022
    Assignees: SAFRAN LANDING SYSTEMS, SAFRAN LANDING SYSTEMS CANADA INC.
    Inventors: Graeme Peter Arthur Klim, Justin Guang Yuang Cheng, Andrew Michael Ellis
  • Patent number: 11448084
    Abstract: A mechanical reduction gear for a turbomachine, in particular for an aircraft, including a first sun gear having a central axis forming a main axis of the reduction gear, a ring gear, planet gears, a planet carrier, and at least one electric generator, in which the electric generator has a first set of electromagnetic elements and a second set of electromagnetic elements, wherein one among the first and second set of electromagnetic elements is a first set of coils, each coil of this first set of coils being wound around a direction parallel to the main axis, and in which the other among the first and second set of electromagnetic elements is configured to induce a current in the first set of coils when it is driven with a relative movement with respect to the first set of coils.
    Type: Grant
    Filed: January 5, 2021
    Date of Patent: September 20, 2022
    Assignee: SAFRAN TRANSMISSION SYSTEMS
    Inventors: Clément Paul René Niepceron, Boris Pierre Marcel Morelli, Florian Rappaport, Bernard Guy Antoine Charpentier
  • Patent number: 11451162
    Abstract: The invention concerns a method for controlling an assembly of at least two inverters (1a, 1b) in an electricity generating system with parallel inverters. The method comprises the implementation by at least one data processing unit (2a, 2b) of the steps: (a) for each inverter (1a, 1b) of the assembly, obtaining an input duty factor (PWMi) of an input signal (Si) received by the inverter (1a, 1b), (b) calculating a mean duty factor (PWMm) from the input duty factors (PWMi), (c) modulating and synchronising the input signal (Si) received by each inverter (1a, 1b) into an output signal (So) having an output duty factor (PWMo) corresponding to the mean duty factor (PWMm).
    Type: Grant
    Filed: September 30, 2019
    Date of Patent: September 20, 2022
    Assignee: SAFRAN ELECTRICAL & POWER
    Inventors: Ashvin Jankee, Guillaume Capron, Frédéric Pailhoux, Pascal Morin, Sonia Dhokkar