Patents Assigned to SNECMA
  • CAPACITIVE SYSTEM FOR CORRECTING THE POGO EFFECT WITH SEMI-CENTERED DISCHARGE TUBE CAPABLE OF BEING POSITIONED IN A BEND
    Publication number: 20180030928
    Abstract: A pogo effect corrector system for a feed system for feeding a rocket engine with liquid propellant, the corrector system comprising: a feed pipe part for feeding liquid propellant that is configured to be connected both upstream and downstream to a liquid propellant feed pipe of the feed system; and a hydraulic accumulator comprising a tank connected to the feed pipe part via at least one communication orifice; the corrector system being characterized in that: at least a portion of the feed pipe part is at least partly surrounded by the inner volume of the tank; with each cross-section of said portion relative to its central axis being at least partly surrounded by the corresponding cross-section of the inner volume of the tank, in such a manner that the corresponding cross-section of the inner volume of the tank is off-center relative to said cross-section of said portion.
    Type: Application
    Filed: January 29, 2016
    Publication date: February 1, 2018
    Applicant: SNECMA
    Inventors: Cyril Paul Denis VERPLANCKE, Mathieu Henry Raymond TRIGER, Jesus Angel HUMANES ASENSIO, Jean-Luc Marcel Rene PATTYN, Ivan MARTINEZ PEREZ
  • Vortex generators placed in the interblade channel of a compressor rectifier
    Patent number: 9879564
    Abstract: A compressor rectifier of a turbomachine including a plurality of stationary blades extending in a circular fashion between an inner shroud and an outer shroud that are concentric and define interblade channels forming an air duct in which air to be compressed flows, the inner shroud including at least one vortex generator extending into the air duct to reduce corner vortices. The vortex generator is positioned axially in the interblade channel, between the axial position of a leading edge of the blades and those of a trailing edge thereof.
    Type: Grant
    Filed: March 7, 2013
    Date of Patent: January 30, 2018
    Assignee: SNECMA
    Inventors: Agnes Claire Marie Pesteil, Vincent Paul Gabriel Perrot, Fatma Ceyhun Sahin
  • Compressor guide-vane stage for a turbine engine including a gasket between a vane and a shroud of the guide-vane stage
    Patent number: 9879562
    Abstract: A compressor guide-vane stage for a turbine engine, the stage comprising two coaxial shrouds, respectively an inner shroud (120) and an outer shroud, with vanes (124) extending between them, the radially inner ends of the vanes being engaged with clearance (125) in orifices in the inner shroud and being secured to the inner shroud by means of a polymerizable sealing resin (126), the guide-vane stage being characterized in that a gasket (140) is mounted on the radially inner end of each vane, the gasket including a slit through which the vane passes and bearing against the radially inside surface of the shroud or in the proximity of said surface, in order to limit the passage of resin through the above-mentioned clearance while the resin is being applied to the inside surface of the shroud.
    Type: Grant
    Filed: April 4, 2013
    Date of Patent: January 30, 2018
    Assignee: SNECMA
    Inventor: Eric Raymond Jean Vatin
  • Blank casting for producing a turbine engine rotor blade and process for manufacturing the rotor blade from this blank
    Patent number: 9879538
    Abstract: A blank casting for producing a turbine engine rotor blade, with a vane connected by a platform to a root, is provided. The root has an axial machining allowance intended to be removed by machining from each of its axial extremities. At least one of the axial extremities of the root includes at least one transverse channel that extends over the entire transverse width of the root and whose depth is greater than the machining allowance. A process for obtaining the blade by machining this blank casting is also provided.
    Type: Grant
    Filed: March 18, 2014
    Date of Patent: January 30, 2018
    Assignee: SNECMA
    Inventors: Alexandre Gimel, Arnaud Negri, Denis Gabriel Trahot
  • Aircraft engine annular shroud comprising an opening for the insertion of blades
    Patent number: 9879549
    Abstract: An aircraft engine annular shroud includes, on its internal surface, a peripheral annular groove able to accept a plurality of blade roots; an insertion opening for inserting the blade roots into the annular groove; and a closure device for closing off the insertion opening.
    Type: Grant
    Filed: May 3, 2012
    Date of Patent: January 30, 2018
    Assignee: SNECMA
    Inventor: Laurent Gilles Dezouche
  • Hydraulic device for changing the pitch of a propeller
    Patent number: 9879552
    Abstract: A hydraulic device for changing the pitch of a propeller including a piston rod actuated by a hydraulic fluid, the piston rod including at its end a clevis mount able to provide a connection for transmitting the movements of the piston rod so as to change the pitch of at least one propeller, a thread nut held in position on the clevis of the piston rod by a fastener, the nut being able to collaborate with a threaded rod in order to provide a connection.
    Type: Grant
    Filed: September 30, 2011
    Date of Patent: January 30, 2018
    Assignee: SNECMA
    Inventors: Frédéric Brettes, Alain François Jean Lavie, Dominique Raulin
  • Turbomachine comprising a plurality of fixed radial blades mounted upstream of the fan
    Patent number: 9879561
    Abstract: A bypass turbine engine including: an inner casing, an inter-duct casing and an outer casing so as to define a primary duct between the inter-duct casing and the inner casing, and a secondary duct between the inter-duct casing and the outer casing; a rotary shaft including, at an upstream end, a movable fan with radial blades of which the free ends face the outer casing to compress an air flow at least in the secondary duct; a plurality of variable-pitch radial stator vanes mounted upstream of the movable fan so as to deflect the incident axial air prior to it being axially rectified by the movable fan in the secondary duct; and a system for individually adjusting the pitch of the radial vanes including a single control ring and rods for connecting the control ring to each of said radial vanes, is provided.
    Type: Grant
    Filed: February 19, 2015
    Date of Patent: January 30, 2018
    Assignee: SNECMA
    Inventors: Jean-Loic Herve Lecordix, Nils Bordoni, Guillaume Patrice Kubiak
  • Sealing of turbine engine enclosures produced by brush seal and labyrinth
    Patent number: 9879607
    Abstract: A sealing device for an enclosure of a turbine engine formed by an assembly of juxtaposed rotating and/or static bodies is provided. The sealing device includes at least one brush seal having a brush body, carried by at least one first member, and bristles extending from the brush body and arranged so as to rub against at least one second member rotatable relative to the first member, so as to produce a pressure difference between the inside of said enclosure and its outer environment. The device further includes a labyrinth-type seal, the labyrinth being positioned in series with the brush seal between the inside of the enclosure and its outer environment.
    Type: Grant
    Filed: December 3, 2013
    Date of Patent: January 30, 2018
    Assignee: SNECMA
    Inventors: Antoine Robert Alain Brunet, Delphine Leroux, Gilles Aouizerate
  • Method for removing a turbofan engine using a heating device
    Patent number: 9878407
    Abstract: A method for removing a twin-spool turbine including a front fan, a HP module with a HP rotor, and a LP turbine module, an intermediate casing including a support bearing for the HP rotor, the HP rotor being retained in the bearing by a link nut, the method including inserting a tool for unscrewing the link nut after having released access to the link nut, and preheating the link nut before starting the unscrewing tool.
    Type: Grant
    Filed: May 2, 2013
    Date of Patent: January 30, 2018
    Assignee: SNECMA
    Inventors: Fabrice Tailpied, Herve Dagron, Cedric Mustiere
  • Method of making a metal reinforcing member for a blade of a turbine engine
    Patent number: 9874103
    Abstract: A method of making a metal reinforcing member that is to be mounted on a leading edge or a trailing edge of a composite blade of a turbine engine, the method including: shaping two metal sheets, positioning them on either side of a core including at least one recess that is to form a mold for a spacer for positioning the reinforcing member, assembling them together under a vacuum, conforming them against the core by hot isostatic compression, and cutting them to separate the reinforcing member and release the core.
    Type: Grant
    Filed: May 31, 2013
    Date of Patent: January 23, 2018
    Assignee: SNECMA
    Inventors: Gilbert Michel Marin Leconte, Gilles Charles Casimir Klein, Jean-Michel Patrick Maurice Franchet, Dominique Magnaudeix
  • Monitoring of an aircraft propulsion system
    Patent number: 9873523
    Abstract: Monitoring the propulsion system of an aircraft includes selecting elements representative of operation of the propulsion system, modeling the propulsion system by a model including the selected elements, a set of exogenic parameters of the propulsion system and interdependence relations between the elements, operation of a given element being modelled by at least one endogenic parameter dependent on at least one of the exogenic parameters and/or on at least one parameter of another element, and analyzing elements, the analysis of the given element including the expression of the at least one endogenic parameter of the given element as a function only of exogenic parameters of the propulsion system and being made by layers of different levels, a layer of a given level being capable of taking account of at least one parameter that is the result of a layer of a different analysis level of another element.
    Type: Grant
    Filed: October 5, 2015
    Date of Patent: January 23, 2018
    Assignee: SNECMA
    Inventor: Guillaume Bothier
  • Linear gasket for an inter-blade platform
    Patent number: 9869323
    Abstract: A linear gasket for an inter-blade platform that presents a length, the gasket including a linear base for fastening to the inter-blade platform and a linear lip projecting from the linear base, the linear lip including a linear distal end portion configured to contact a pressure side wall or a suction side wall of a blade, a linear groove being formed between the linear base and the linear lip over at least a fraction of a length of the linear gasket. The linear distal end portion includes at least one linear slit extending over at least a fraction of the length of the gasket.
    Type: Grant
    Filed: February 15, 2013
    Date of Patent: January 16, 2018
    Assignee: SNECMA
    Inventor: Anne-Laure Ravier
  • Sealing device between two axisymmetric coaxial parts
    Patent number: 9869193
    Abstract: A sealing device between two axisymmetric coaxial parts, includes an elastic segment, two holding elements located on each side of the annular segment, an annular spacer arranged between the two holding elements, wherein the annular spacer has a notch around its peripheral rim; the annular elastic segment has a hooking element at each of its free ends, adapted to cooperate with the notch of the annular spacer, and to hold the elastic segment in a pre-holding position by elastic return force.
    Type: Grant
    Filed: January 7, 2013
    Date of Patent: January 16, 2018
    Assignee: SNECMA
    Inventors: Serge René Morreale, Arnaud Jean-Marie Pierrot
  • Test bench combining high-frequency tribological stress and oligocyclic fatigue, on a blade disk of turboshaft engine of an aircraft including a test piece having a portion with a shape of a blade root of a rotor and is engaged in a groove shape complementary to another test piece
    Patent number: 9869621
    Abstract: A test rig combining high-frequency tribological stress and low-cycle fatigue. The test rig includes a first test piece which is fixed to a frame and defines at least one bearing surface, a second test piece which is connected to an actuator for loading the second test piece so that it bears against the at least one bearing surface of the first test piece, a heater configured for heating the test pieces and a vibration generator, such as a shaker, for loading the test pieces in a vibratory manner so as to carry out a fretting fatigue and low-cycle and high-cycle fatigue test. One of the test pieces includes a portion in the shape of a turbine engine rotor blade root and which is inserted in a groove having a shape that is substantially complementary to the other test piece so as to reproduce a turbine engine blade-disc attachment.
    Type: Grant
    Filed: May 9, 2014
    Date of Patent: January 16, 2018
    Assignees: TURBOMECA, SNECMA
    Inventors: Laurent Houze, Jean Philippe Lapuyade, Franck Vernis, François Vogel, Jean Vincent Manuel Meriaux
  • Compacting and injection mold for a fiber preform for fabricating a turbine engine guide vane made of composite material
    Patent number: 9868235
    Abstract: A compacting and injection mold for a fiber preform is for use in fabricating a turbine engine guide vane out of composite material. The mold includes a shell forming a trough that is to receive the fiber preform and that is closed in leaktight manner by bottom and top covers, compacting blocks arranged inside the trough each having a surface pressing normally against a surface of the fiber preform that is to be compacted, and closure blocks arranged inside the trough. Each closure block has a surface pressing normally against a surface of a compacting block and does not have a surface in contact with the fiber preform.
    Type: Grant
    Filed: May 3, 2012
    Date of Patent: January 16, 2018
    Assignee: SNECMA
    Inventors: Romain Plante, Lise Lacroix, Olivier Patrigeon, Jean-Pierre Cauchois, Pascal Burek
  • Single-piece blisk for turbomachine fan comprising an upstream and/or downstream recess making its blades more flexible
    Patent number: 9863252
    Abstract: The invention relates to a single-piece fan blisk (14) for a turbojet, this blisk (14) comprising a hub (16) with a general shape of revolution about a rotation axis (AX) and comprising an external peripheral face (18) of revolution extending radially towards the rotation axis at an upstream face (19) and a downstream face both of which are in the form of rings. This hub (16) supports radially oriented blades (17) at its external peripheral face (18), each comprising a base through which it is connected to this external peripheral face (18), each blade (17) having a leading edge (22) and a trailing edge (23) that are radially oriented. The spacing between the upstream face (19) and the downstream face of the hub (16) along the rotation axis (AX) is less than the distance separating the leading edge (22) from the trailing edge (23) of each blade.
    Type: Grant
    Filed: November 16, 2015
    Date of Patent: January 9, 2018
    Assignee: SNECMA
    Inventors: Damien Merlot, Etienne Ide, Philippe Gérard Edmond Joly
  • Isostatic suspension of a turbojet by rear double support
    Patent number: 9863273
    Abstract: The invention relates to a bypass turbojet comprising an exhaust housing having a central hub (13) and connecting means (11) that can transmit the forces generated by the turbojet to the structure of the aircraft that it propels, said connection means being two arms extending radially from the central hub in order to cross the cold flow of said turbojet and being characterized in that they are secured to said central hub and positioned in a diametrically opposed manner in relation to each other. An additional connection means (14) extends between the hub (13) and the area (9) for securing the exhaust housing to the structure (12) of the aircraft in order to transmit the exceptional dimensioning loads, said connection means being on standby during normal use, without any transmission of force between said hub and said area.
    Type: Grant
    Filed: August 21, 2014
    Date of Patent: January 9, 2018
    Assignee: SNECMA
    Inventors: Francois Robert Bellabal, Francois Gallet, Mathieu Ange Poisson
  • Heat exchanger for a turbo engine
    Patent number: 9863320
    Abstract: The invention relates to a heat exchanger of an air circulation channel of a turbomachine, the heat exchanger being configured so as to have fluid to be cooled passing through it and including a plurality of fins protruding from a support surface, the heat exchanger being characterized in that each fin includes a base and a preferably continuous leading face which extends axially from the base in the air circulation direction while tapering from upstream to downstream along an axis parallel with the support surface.
    Type: Grant
    Filed: December 19, 2014
    Date of Patent: January 9, 2018
    Assignee: SNECMA
    Inventors: Imane Ghazlane, Gabriela Philippart
  • Turbomachine casing
    Patent number: 9863270
    Abstract: A turbomachine casing including a substantially cylindrical wall and an annular one-piece acoustic insulation panel mounted inside the wall, the panel including an annular surface that is radially external opposite a radially internal annular surface of the wall, wherein the wall includes on its internal angular surface first projecting members which bear axially against second projecting members belonging to the external annular surface of the panel and which are fixed to these second members in a dismountable manner.
    Type: Grant
    Filed: November 4, 2013
    Date of Patent: January 9, 2018
    Assignee: SNECMA
    Inventors: Romain Plante, Romain Coulon, Geoffroy De La Chapelle, Paul Follin, Florent Rognin
  • Correction of a temperature measurement of a thermometric resistance-type temperature probe
    Patent number: 9863797
    Abstract: The invention relates to a temperature measurement method using a thermometric resistance-type temperature probe (1) comprising at least two electroconductive sensitive elements (3, 4) on the same substrate (2), wherein different parameters representative of the strength of the electric current circulating in one of said sensitive elements (3, 4) are measured, and a correction, according to said strength of the electric current circulating in said sensitive element (3, 4), is applied to a signal representative of a temperature measurement generated from the other one of said sensitive elements (3, 4), in order to correct an error created as a result of the self-heating by the Joule effect of said sensitive element (3, 4) affecting the other one of said sensitive elements (3, 4).
    Type: Grant
    Filed: April 23, 2013
    Date of Patent: January 9, 2018
    Assignee: SNECMA
    Inventor: Maurice Georges Vernochet