Patents Assigned to SAFRAN
  • Patent number: 10279889
    Abstract: A hydraulic ram comprising a fixed support, a cylinder that is movable in translation relative to the support, a piston secured inside the cylinder delimiting two chambers with the cylinder and a device for supplying the chambers with hydraulic fluid upstream from the fixed support. The ram is characterized by the fact that the supply device comprises telescopic channels, each telescopic channel comprising two tubular elements sliding one into the other, a first tubular element being rigidly connected to the fixed support at one end and the second tubular element being rigidly connected to the cylinder at at least two points separated from each other along a generatrix of the cylinder. The invention is applicable to controlling the pitch of the blades of a turbine engine propeller.
    Type: Grant
    Filed: September 22, 2014
    Date of Patent: May 7, 2019
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Olivier Belmonte, Augustin Curlier
  • Patent number: 10280839
    Abstract: An acoustic treatment panel including a cellular structure core sandwiched between a solid skin and a perforated skin, and a plurality of domes made of porous fabric and extending from at least one of the skins into the insides of the cells of the cellular structure towards the other skin so as to define at least two resonant cavities inside each cell of the cellular structure.
    Type: Grant
    Filed: September 23, 2015
    Date of Patent: May 7, 2019
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Georges Jean Xavier Riou, Jacky Novi Mardjono
  • Patent number: 10279896
    Abstract: An aircraft spring assembly having a spring, an end fitting including a spring engagement formation arranged to be mechanically coupled to an end region of the spring and a coupling formation for coupling the spring assembly to an aircraft anchor point. The coupling formation includes a load bearing surface via which loads from the anchor point can be transmitted into the spring assembly. The assembly further includes an integral damping member provided within the load path between the load bearing surface of the coupling formation and the end region of the spring.
    Type: Grant
    Filed: May 17, 2016
    Date of Patent: May 7, 2019
    Assignee: SAFRAN LANDING SYSTEMS UK LTD
    Inventors: Andraz Vatovec, Paul Greenwood, Andrew Paddock
  • Patent number: 10280776
    Abstract: The present invention relates to a turbine assembly (10) of a turbine engine (1), comprising at least: a first bladed rotor (12), a bladed stator (13) and a second bladed rotor (14) arranged in series, the rotors (12, 14) being mounted on a shaft (2); a sealing plate (20) extending between the stator (13) and the shaft (2) and separating a first recess (C1) arranged between the first rotor (12) and the stator (13), from a second recess (C2) arranged between the stator (13) and the second rotor (14); and pressure-reducing means (300, 31) positioned inside the first recess (C1), the assembly being characterized in that said pressure-reducing means (300, 31) comprise a plurality of substantially radial recompression fins (300) extending into the first recess (C1).
    Type: Grant
    Filed: December 17, 2015
    Date of Patent: May 7, 2019
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Damien Bernard Quelven, Jean-Baptiste Vincent Desforges, Maurice Guy Judet, Ba-Phuc Tang
  • Patent number: 10280758
    Abstract: A composite vane for a low-pressure compressor of an axial-flow turbomachine, wherein the vane comprises a platform and an aerodynamic airfoil having a leading edge and a trailing edge. The airfoil extends into the primary flow of the turbomachine. The airfoil includes a body extending from the leading edge to the trailing edge and a reinforcement of the leading edge of the airfoil. The reinforcement comprises a reinforcing sheet, which extends from the leading edge to the trailing edge, and which is arranged in the thickness of the body in such a way as to reinforce it. In addition, the reinforcement comprises a shell forming the leading edge and which is integral with the sheet. The sheet is a titanium sheet, and the body includes a composite material having an organic matrix charged with fibers. This configuration improves the rigidity and the resistance to corrosion while lightening the airfoil.
    Type: Grant
    Filed: February 25, 2016
    Date of Patent: May 7, 2019
    Assignee: SAFRAN AERO BOOSTERS SA
    Inventor: Jean-François Cortequisse
  • Patent number: 10280755
    Abstract: When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y, Zadim given in Table 1, in which the coordinate Zadim is the quotient D/H where D is the distance of the point under consideration from a first reference plane P0 situated at the base of the nominal profile, and H is the height of said profile measured from the first reference plane to a second reference plane P1. The measurements D and H are taken radially relative to the axis of the turbine, while the X coordinate is measured in the axial direction of the turbine.
    Type: Grant
    Filed: December 29, 2016
    Date of Patent: May 7, 2019
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Maxime Didier Delabriere, Vincent Nicolas Leonardon, Daniel Marius Man, Pierre Hervé Marche
  • Patent number: 10279913
    Abstract: Described is a breakover mechanism for a passenger seat that includes a frame member with a rear portion attached to two opposing sides of a seat back of the passenger seat wherein the frame member is at least partially disposed under a seat pan of the passenger seat, at least one moving portion attached to a forward portion of the frame member, a carriage portion fixedly attached to the seat pan; and a single point mechanism attached to the carriage portion. Once a threshold loading condition occurs, the single point mechanism changes states to facilitate movement of the moving portion relative to the carriage portion.
    Type: Grant
    Filed: June 20, 2016
    Date of Patent: May 7, 2019
    Assignee: Safran Seats USA LLC
    Inventors: Girish J. Malligere, Nahum Madrid, Michael T. Murray, Michael Willey
  • Patent number: 10280940
    Abstract: The present application is concerned with a blading structure of a compressor of an axial turbomachine for an aircraft. The blading structure includes a wall, such as a composite internal shroud with an organic matrix, which is intended to radially delimit a primary annular flow of the turbomachine and which comprises a fastening socket. The structure additionally has a blade fastened in the fastening socket and extending radially with respect to the wall, and a fastening layer at the interface between the blade and the socket. The interface includes asperities hugging the fastening layer, so as to ensure anchoring by engagement of material in order to fasten the blade in the socket by bonding. The present application also proposes a low-pressure compressor with an internal shroud with sockets bonded to blades.
    Type: Grant
    Filed: May 19, 2016
    Date of Patent: May 7, 2019
    Assignee: SAFRAN AERO BOOSTERS SA
    Inventor: Jean-François Cortequisse
  • Patent number: 10279308
    Abstract: A process for treating effluent gas containing polycyclic aromatic hydrocarbons includes a step of spray scrubbing with a mineral oil in order to trap the hydrocarbons, wherein the mineral oil includes a mixture of aromatic mineral oil and naphthenic mineral oil.
    Type: Grant
    Filed: March 4, 2015
    Date of Patent: May 7, 2019
    Assignee: SAFRAN CERAMICS
    Inventors: Jean-François Potin, Bernard Delperier
  • Publication number: 20190126532
    Abstract: Method for forming a riblet on a component and riblet mould. This invention relates to a method for forming a riblet (3) on a component (1), characterised in that it comprises steps of: printing (106) the riblet on the component (1), comprising applying a film (1) comprising a riblet imprint (6) on the component (1), and peeling (108) the film (4) so as to separate the riblet imprint (6) from the component (1), after printing (106). This invention also relates to a riblet mould (3), the mould comprising a film (4) in which a riblet imprint (6) is formed, the film (4) being adapted to be separated from a component (1) on which a riblet (3) has been printed by means of the riblet mould (3), by peeling the film (4).
    Type: Application
    Filed: June 2, 2017
    Publication date: May 2, 2019
    Applicant: SAFRAN
    Inventors: Nicolas Pierre LANFANT, Florence CASTAGNET, Thierry CHAUVIN, Emilie GONCALVES, Nicola PICCIRELLI, Loïc SORGNARD
  • Publication number: 20190128118
    Abstract: A compressor for a turbine engine includes an annular row of blades including a first blade with an extrados surface and a second blade with an intrados surface; and a connecting surface joining the intrados surface to the extrados surface, the connecting surface having a bulge of volume VB and a recess of volume VC, the bulge and recess forming a contouring 3D. The volume of the bulge VB is greater than four times the volume VC of the recess, the connecting surface includes a flat or axisymmetric band circumferentially separating the bulge from the recess, and the bottom of the recess being formed against the intrados surface.
    Type: Application
    Filed: October 26, 2018
    Publication date: May 2, 2019
    Applicant: SAFRAN AERO BOOSTERS SA
    Inventor: Stéphane Hiernaux
  • Publication number: 20190128132
    Abstract: A support case for a turbomachine ring sector includes an annular body around a longitudinal axis of the case, and a downstream edge for attachment of the ring sector. The downstream edge extends from the body radially towards the inside of the case. The downstream edge extends circumferentially along a junction region between the body and a fixed vanes stage. The junction region includes a central portion and two lateral portions located on each side of the central portion, along a circumferential direction of the case with respect to its longitudinal axis. The central portion projects radially outwards from the case with respect to the lateral portions.
    Type: Application
    Filed: October 22, 2018
    Publication date: May 2, 2019
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Nicolas Paul TABLEAU, Sebastien Serge Francis Congratel, Antoine Claude Michel Etienne Danis, Maurice Guy Judet, Lucien Henri Jacques Quennehen
  • Publication number: 20190128121
    Abstract: A low-pressure compressor for an axial-flow turbomachine, such as a jet engine, includes an annular row of vanes and a between-vanes passage with a connecting surface that links the pressure surface of a first vane to the suction surface of a second vane of the row. The connecting surface includes a main protuberance which includes a first elevation and a second elevation that are spaced apart from one another.
    Type: Application
    Filed: September 27, 2018
    Publication date: May 2, 2019
    Applicant: SAFRAN AERO BOOSTERS SA
    Inventor: Stéphane Hiernaux
  • Publication number: 20190128122
    Abstract: In an axial turbomachine low-pressure compressor, the compressor, or booster, includes a first vane with an intrados surface, a second vane with an extrados surface, an inter-vane passage with a guiding surface, which connects the intrados surface to the extrados surface delimiting an annular vein, and which has a bulge and a recess forming a so-called 3D contouring geometry, or non-axisymmetric surface. The guiding surface includes an axially symmetrical or substantially flat zone, which axially extends through the inter-vane passage so as to separate the recess from the bulge.
    Type: Application
    Filed: September 27, 2018
    Publication date: May 2, 2019
    Applicant: SAFRAN AERO BOOSTERS SA
    Inventor: Stéphane Hiernaux
  • Publication number: 20190127053
    Abstract: The invention relates to an aircraft undercarriage provided at its bottom end with a rocker arm (2) carrying at least two axles (4, 5), including one in front of a hinge between the rocker arm and the undercarriage and the other behind said hinge. According to the invention, one of the axles is fitted with one or more braked wheels (6) and the other axle is fitted with one or more motor-driven wheels (8).
    Type: Application
    Filed: October 26, 2018
    Publication date: May 2, 2019
    Applicant: SAFRAN LANDING SYSTEMS
    Inventor: Jean-Yves RAVEL
  • Publication number: 20190126894
    Abstract: A piece of electrical equipment for connecting both to at least one electromechanical braking actuator and also to at least one electromechanical drive actuator, the piece of electrical equipment (13a) comprising a housing (30), means for fastening the housing to the undercarriage, and inside the housing: a processor unit (32) arranged to generate a braking motor control signal and a drive motor control signal; a power supply unit (37) arranged to generate an equipment power supply voltage, a braking power supply voltage, and a drive power supply voltage; a power converter unit (40) arranged to generate a braking control voltage and a drive control voltage; and a distribution unit arranged to distribute the braking control voltage to the electromechanical braking actuator and the drive control voltage to the electromechanical drive actuator.
    Type: Application
    Filed: October 29, 2018
    Publication date: May 2, 2019
    Applicant: SAFRAN LANDING SYSTEMS
    Inventor: Brian GOYEZ
  • Publication number: 20190128133
    Abstract: An assembly including a sector of fixed blades for turbomachine distributor including at one circumferential end a protuberance and at another circumferential end a contact surface, such that the protuberance of a sector arrives opposite the contact surface of another adjacent sector, a detachable cap including a surface with anti-wear material, configured to be engaged detachably on the protuberance of the sector, such that the anti-wear material is in contact with the contact surface of the other sector.
    Type: Application
    Filed: October 30, 2018
    Publication date: May 2, 2019
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Jean-Charles Marcel Bernard Coetard, Josserand Jacques Andre Bassery, Raphael Jean Philippe Dupeyre, Etienne Leon Francois
  • Patent number: 10273817
    Abstract: A turbine ring assembly includes a ring support structure and a plurality of CMC ring sectors forming a turbine ring. Each ring sector is K-shaped in radial section, with tabs extending from the outside face of the annular base over end portions of the annular base, the tabs and the end portions of each ring sector being held respectively facing tabs and end portions of ring sectors that are adjacent in the ring. The turbine ring assembly has a plurality of rigid gaskets, each extending axially between adjacent ring sectors, and resilient holder devices exerting a force suitable for holding the gaskets in contact with the end portions or the tabs of two adjacent ring sectors.
    Type: Grant
    Filed: March 31, 2016
    Date of Patent: April 30, 2019
    Assignees: SAFRAN CERAMICS, SAFRAN AIRCRAFT ENGINES
    Inventors: Clément Roussille, Thierry Tesson, Freddy Guilbaud
  • Patent number: 10274956
    Abstract: The invention relates to a method for guiding an aircraft along a reference path, said method comprising: a) when the altitude of the aircraft is greater than a threshold, estimating (E1) a relative location of the aircraft in relation to a taxiing starting point using a map of the platform and reference points on the ground, b) when the altitude of the aircraft is less than said threshold and before the aircraft is located at the taxiing starting point, estimating (E2) a relative location of the aircraft in relation to the taxiing starting point using data relating to the absolute location of the aircraft and the last relative location estimated at step a), c) when the aircraft is located at the taxiing starting point, guiding (E3) the aircraft on the basis of a location of the aircraft relative to the reference path as estimated using data relating to a set of indicators on the ground.
    Type: Grant
    Filed: April 22, 2015
    Date of Patent: April 30, 2019
    Assignee: SAFRAN ELECTRONICS & DEFENSE
    Inventor: Julien Farjon
  • Patent number: 10273977
    Abstract: A rotor, in particular a drum of a low-pressure compressor of a turbojet aero engine, is disclosed. The rotor includes an outer annular wall delimiting a primary annular flow of the turbine engine, sealing devices with two rubbing strips or annular ribs formed on the wall. The rubbing strips cooperate by abrasion with inner shrouds. In addition, the annular wall includes rows of intake orifices for leakages which are arranged between each pair of rubbing strips in order to aspirate the recirculation leakages there. A plenum for leakages is formed inside the rotor by means of a composite partitioning, then evacuates the parasitic flow downstream of the turbine engine via the central shaft.
    Type: Grant
    Filed: June 30, 2016
    Date of Patent: April 30, 2019
    Assignee: SAFRAN AERO BOOSTERS SA
    Inventor: Stéphane Hiernaux