Patents Assigned to SNECMA
  • Method of characterizing an object including, at least locally, a plane of symmetry
    Patent number: 9683969
    Abstract: A method of characterizing an object that includes, at least locally, a plane of symmetry, the method including performing at least one observation of ultrasound transmitted through the object, each observation being performed on an axis perpendicular to the plane of symmetry, each observation resulting from an emission of ultrasound generated along a respective one of the axes and meeting the object along the axis at an angle of incidence other than normal, the ultrasound meeting the object to follow a path that is symmetrical relative to the plane of symmetry.
    Type: Grant
    Filed: July 2, 2013
    Date of Patent: June 20, 2017
    Assignee: SNECMA
    Inventor: Jean-Yves Francois Roger Chatellier
  • Pylon for fixing an aircraft engine having unducted pusher propellers
    Patent number: 9682783
    Abstract: A pylon for fixing an aircraft engine having unducted pusher propellers, the pylon ensuring the fixation of a propulsive system on the boattail of the aircraft, the pylon having a trailing edge, with an upper face and a lower face, for an airflow encountered by the pylon, wherein at least one of the two faces of the upper face and the lower face of the trailing edge is inclinable, at least in part.
    Type: Grant
    Filed: December 7, 2011
    Date of Patent: June 20, 2017
    Assignee: SNECMA
    Inventors: Stéphane Emmanuel Daniel Bensilum, Jean Bertucchi, Gaétan Jean Mabboux
  • Convergent-divergent nozzle for a turbine engine
    Patent number: 9683516
    Abstract: A turbine engine convergent-divergent nozzle including an annular central element and an annular cap arranged coaxially around the central element to co-operate with the central element to define an annular flow channel for a gas stream from the engine. Between a throat section and an ejection section of the nozzle, the central element and the cap present respective internal profiles in longitudinal section that are modeled by curves having respective radii of curvature that are identical in absolute value.
    Type: Grant
    Filed: December 4, 2012
    Date of Patent: June 20, 2017
    Assignee: SNECMA
    Inventors: Matthieu Leyko, Jean Bertucchi, Mathieu Gaillot
  • Labyrinth seal for gas turbine engine turbine
    Patent number: 9683452
    Abstract: A turbine for a gas turbine engine comprising at least one turbine stator and one turbine rotor, said turbine stator comprising at least one inner annular platform, said inner platform comprising a radial wall delimiting at least one cavity between the turbine stator and the turbine rotor, wherein the turbine rotor comprises at least one elongate element positioned substantially axially and defining a sealing baffle in said cavity, and in that the turbine stator comprises at least one element made of abradable material designed to engage with said elongate element of the turbine rotor so as to form a labyrinth seal.
    Type: Grant
    Filed: December 19, 2013
    Date of Patent: June 20, 2017
    Assignee: SNECMA
    Inventors: Florent Pierre Antoine Luneau, Alain Dominique Gendraud, Patrick Joseph Marie Girard, Sebastien Jean Laurent Prestel
  • FAN FOR A TURBOMACHINE
    Publication number: 20170167504
    Abstract: The invention proposes a fan, in particular for a turbomachine of small size such as a jet engine, having a hub ratio which corresponds to the ratio of the diameter of the inner limit of the incoming air stream (26) at the radially inner ends of the leading edges of the fan blades (10), divided by the diameter of the circle around which the outer ends of the fan blades pass, having a value of between 0.20 and 0.265.
    Type: Application
    Filed: November 26, 2014
    Publication date: June 15, 2017
    Applicant: Snecma
    Inventors: Laurent Jablonski, Philippe Gérard Edmond Joly, Christophe Perdrigeon, Damien Merlot, Hervé Pohier
  • Interface device between two turbomachine elements
    Patent number: 9677413
    Abstract: An interface device between first and second turbomachine elements is provided. The interface device includes an annular air inlet structure including opposite first and second parts, designed to come into contact with the first and second turbomachine elements respectively, in which the first part is configured to be in swivel contact with the first element; and an elastic return device that can be placed around the air inlet structure and designed to come into contact with at least the first turbomachine element.
    Type: Grant
    Filed: May 19, 2014
    Date of Patent: June 13, 2017
    Assignee: SNECMA
    Inventors: Arthur Cohin, Audrey Charrie, Florent Gant, Aurelien Rene-Pierre Massot
  • One-block bladed disk provided with blades with adapted foot profile
    Patent number: 9677404
    Abstract: A one-block bladed disk includes blades, a leading edges of which has sweep and dihedral angles, both strongly variable and increasingly large upon approaching a connection to a hub to improve mechanical strength of the whole and obtain good distribution of gas flow over the height of the blade.
    Type: Grant
    Filed: October 8, 2012
    Date of Patent: June 13, 2017
    Assignee: SNECMA
    Inventors: Didier Merville, Lucie Galons, Vincent Perrot, Hanna Reiss
  • Axisymmetrical intermediate case part including an insert positioned in an annular groove
    Patent number: 9677425
    Abstract: An axisymmetrical portion for an aircraft turbojet engine intermediate case intended to protrude downstream from an outer axisymmetrical portion of the intermediate case is provided. The axisymmetrical portion includes an annular groove radially open outwards, and at least one insert laid out inside the groove, which covers each internal face of the groove and which is radially open outwards.
    Type: Grant
    Filed: July 26, 2013
    Date of Patent: June 13, 2017
    Assignee: SNECMA
    Inventors: Richard Lavignotte, Patrick Jean-Louis Reghezza
  • System for controlling the pitch of the propeller blades of a turbomachine, and a turbomachine with a propeller for an aircraft with such a system
    Patent number: 9677408
    Abstract: A control system includes a power actuator coaxial with the axis of rotation of the propeller, and a transmission device connecting the power actuator to pivots, of the blades to be controlled, arranged substantially radially with respect to the axis of rotation. The actuator is a rotary jack whose mobile part rotates about the axis of rotation and is connected to the transmission device by a mobile mechanical connection which transforms the rotation imparted by the mobile part of the jack about the axis of rotation into a rotation of the blades about the axes of the pivots which are perpendicular to the axis of rotation.
    Type: Grant
    Filed: April 29, 2014
    Date of Patent: June 13, 2017
    Assignee: SNECMA
    Inventors: Sébastien Tajan, Christophe Jacquemard, Adrien Fabre
  • FLOW REGULATING SYSTEM FOR SUPPLYING PROPELLANT FLUID TO AN ELECTRIC THRUSTER OF A SPACE VEHICLE
    Publication number: 20170159647
    Abstract: A system for regulating the flow rate of a propellant fluid for an electrical thruster of a space vehicle, the vehicle including a tank of propellant fluid and a flow rate regulator connected to the outlet of said tank; the flow rate regulator including a heater element controlled by a computer and adapted to heat the propellant fluid and to modify its physical properties so as to vary the flow rate of propellant fluid leaving the tank; said system being characterized in that the computer also includes a plurality of empirical calibration curves that have been determined empirically for defining the flow rate of propellant fluid as a function of the magnitude of heating and as a function of environmental parameters, such that said computer also performs a function of determining the flow rate of the propellant fluid.
    Type: Application
    Filed: December 9, 2014
    Publication date: June 8, 2017
    Applicant: SNECMA
    Inventors: Vanessa Vial, Anthony Lorand, Kevin Giboudeaux, Vaitua Leroi
  • Arrangement of an oblique-contact seal in a trapezoidal groove
    Patent number: 9671021
    Abstract: An arrangement of a biconical annular seal having a laid down V shaped cross-section, in an annular groove having a trapezoid shaped cross-section, a small base of the trapezoid corresponding to a cylindrical bottom of the groove and being radially inwardly open at a great base of the trapezoid. The seal includes a radially outer annular heel and two generally conical annular wings extending radially inwardly from the heel, an inner radial end of each wing being axially bearing against an associated wall of the groove. The seal is mounted in the groove such that the heel of the seal is located radially distal to a bottom of the groove.
    Type: Grant
    Filed: October 11, 2012
    Date of Patent: June 6, 2017
    Assignees: SNECMA, CENTRE NATIONAL D'ETUDES SPATIALES CNES
    Inventors: Christelle Lea Branchet-Cohen, Karine Sandra Christel Lenain
  • Process for injection moulding a composite part
    Patent number: 9669570
    Abstract: A method of injection molding a part made of composite material is provided. The method includes placing a preform in a mold; injecting a resin into the mold so as to impregnate the preform; unmolding the part after curing the resin; and subjecting the resin and the preform to pressure inside the mold while the resin is curing.
    Type: Grant
    Filed: May 2, 2012
    Date of Patent: June 6, 2017
    Assignee: SNECMA
    Inventors: Thierry Godon, Bruno Jacques Gérard Dambrine, Eduardo Antonio Julian Ruiz, François Trochu
  • Method of making protective reinforcement for the leading edge of a blade
    Patent number: 9664201
    Abstract: A method of making a reinforcement for reinforcing a leading edge of a blade, the method including depositing a metal coating on the leading edge by thermal spraying in compression. A blade, for example a blade for a turbine engine, a helicopter, or a propeller, can have the leading edge protected by such a reinforcement.
    Type: Grant
    Filed: August 9, 2012
    Date of Patent: May 30, 2017
    Assignee: SNECMA
    Inventors: Laurent Paul Dudon, Antonio Cremildo Arantes
  • Device for suspending a turbojet engine
    Patent number: 9664112
    Abstract: A turbojet is suspended by attachments including hinged links. An attachment includes a support including three branches with passages through which a pin passes, the pin being oriented generally parallel to a direction that is tangential to a casing and being hinged to a central branch of the support by a ball joint.
    Type: Grant
    Filed: December 20, 2011
    Date of Patent: May 30, 2017
    Assignee: SNECMA
    Inventors: Wouter Balk, Thomas Alain Christian Vincent
  • Hydraulic system for controlling the orientation of fan blades
    Patent number: 9663218
    Abstract: A hydraulic system for controlling orientation of fan blades in a turbine engine including at least one set of adjustable pitch fan blades actuated by actuators that are connected to a hydraulic pump, and a small pitch protection valve controlled by an associated solenoid valve to make it possible on the ground, when the orientation of the blades is substantially perpendicular to the axis of the turbine engine, to pass from a first operating zone in which a speed of pitch variation of the blades is low to a second operating zone in which a speed of pitch variation is considerably higher, wherein operating pressure of the hydraulic pump is controlled by the solenoid valve controlling the small pitch protection valve to define two outlet levels corresponding to the two operating zones.
    Type: Grant
    Filed: August 3, 2012
    Date of Patent: May 30, 2017
    Assignee: SNECMA
    Inventors: Caroline Frantz, Regis Michel Paul Deldalle
  • Guidance of turbine engine shafts
    Patent number: 9664117
    Abstract: A turbine engine including a power gear box shaft, a turbine shaft, a connecting part of annular shape by which one end of the power gear box shaft and one end of the turbine shaft are connected in a rotationally fixed manner, a structural housing, and a guide bearing for guiding the connecting part relative to the housing, is provided. The guide bearing is mounted between the connecting part and the housing and includes an external ring mounted on the housing, an internal ring mounted on the connecting part, and at least one rolling element configured to enable the external ring to roll around the internal ring. The guide bearing is configured to form a ball joint link enabling a relative angular displacement of its external ring with respect to its internal ring.
    Type: Grant
    Filed: December 5, 2013
    Date of Patent: May 30, 2017
    Assignee: SNECMA
    Inventors: Olivier Belmonte, Julien Austruy, Mathieu Perrier
  • Removable mask for a turbomachine blade or distributor sector platform
    Patent number: 9657405
    Abstract: A removable mask for a platform or a nozzle sector of a turbine engine blade, the blade or sector configured to be covered in an electrolytic deposit, the mask including a mechanism to engage on the platform and a mechanism to cover outer surfaces of the platform that are not to be covered by the electrolytic deposit.
    Type: Grant
    Filed: April 14, 2011
    Date of Patent: May 23, 2017
    Assignee: SNECMA
    Inventors: Pascal Etuve, Frederic Lagrange, Patrick Marquereau, Pascal Sainz
  • Composite material reinforcing part of pi-shaped section, in particular a platform for a turbine engine fan, and its method of fabrication
    Patent number: 9657583
    Abstract: A reinforcing part of ?-shaped section made out of composite material, and a method of making the part, the method including: making a first set of layers of interlinked yarns by three-dimensional weaving to form a first fiber blank portion to form a base preform; making a second set of layers of interlinked yarns by three-dimensional weaving to form a second fiber blank portion to form a stiffener preform, yarns of the second set being interlinked with yarns of the first set by weaving over a central interlinked strip that flares towards side edges of the first fiber blank portion in a zone corresponding to the step of the base; shaping the two fiber blank portions to obtain a single-piece fiber preform having a portion forming a base preform and a portion forming a stiffener preform; and depositing a resin in the fiber preform to form a matrix.
    Type: Grant
    Filed: January 7, 2013
    Date of Patent: May 23, 2017
    Assignee: SNECMA
    Inventors: Yann Marchal, Jean-Noel Mahieu
  • Cooled vane of a high-pressure turbine
    Patent number: 9657579
    Abstract: The invention relates to a movable vane of a turbomachine comprising a blade (12) with inner cooling cavities and a root (11) by which means the vane can be mounted on a rotor disk, the root comprising at least two channels (11a) communicating with said inner cavities and leading to the base (11b) thereof, said base comprising at least two openings (11b1, 11b2) through which the channels open up, and a calibrating plate (20) provided with calibrated perforations (21, 22) corresponding to said openings being attached to the base (11b) of the root. The vane is characterized in that a mechanical means (25, 26; 11m1, 11m2) forming a sealing barrier between the two openings is arranged between the plate and the base of the root.
    Type: Grant
    Filed: September 12, 2013
    Date of Patent: May 23, 2017
    Assignee: SNECMA
    Inventors: Erwan Daniel Botrel, Charlotte Marie Dujol
  • Method for mounting an acoustic panel in a housing of a turbomachine and turbomachine comprising an acoustic panel
    Patent number: 9657644
    Abstract: A method for mounting an acoustic panel on the inner surface of an annular housing of an axial turbomachine, the cylindrical acoustic panel comprising at least one longitudinal slot so as to define two opposing ends, the method comprising: bringing the two opposing ends closer together so as to reduce the cylinder radius of the acoustic panel; inserting the acoustic panel into the fan casing when the opposing ends are close together; deploying the opposing ends so as to increase the cylinder radius of the acoustic panel; and securing the acoustic panel to the housing by gluing.
    Type: Grant
    Filed: September 11, 2013
    Date of Patent: May 23, 2017
    Assignee: SNECMA
    Inventors: François Sfarti, François Marie Paul Marlin