Patents Assigned to SNECMA Moteurs
  • Convergent-divergent turbojet nozzle
    Patent number: 6993914
    Abstract: The present invention relates to a convergent-divergent turbojet nozzle (1) comprising driven divergent flaps (4a), follower divergent flaps (4b) interposed between the driven flaps, and means (32) for supplying cooling air to the follower flaps (4b), said follower flaps (4b) having a box structure and having lateral openings for delivering cooling air towards the inner face of said driven flaps (4a), in such a way as to limit the heating up of these flaps when the turbojet is in operation.
    Type: Grant
    Filed: August 11, 2004
    Date of Patent: February 7, 2006
    Assignee: Snecma Moteurs
    Inventors: Jackie Prouteau, Raphaël Curtelin, Guy Lapergue, Didier Feder
  • Drum, in particular a drum forming a turbomachine rotor, a compressor, and a turboshaft engine including such a drum
    Patent number: 6991433
    Abstract: The drum of the invention is generally in the form of a body of revolution about a longitudinal axis, being made of a metal alloy and extending between an upstream end and a downstream end along a curved profile capable of being circumscribed in an annular envelope extending around said longitudinal axis, said profile extending radially about a surface of revolution presenting a generatrix line, said downstream end being provided with a stiffener. In characteristic manner, said stiffener is provided with at least one composite assembly mounted on said downstream end, said composite assembly comprising fibers and a polymer matrix. The drum is preferably for use in constituting a rotor of a low pressure compressor.
    Type: Grant
    Filed: September 23, 2003
    Date of Patent: January 31, 2006
    Assignee: Snecma Moteurs
    Inventor: Claude Mons
  • Device for fastening a fluid duct to a turbojet casing
    Publication number: 20060016194
    Abstract: A device for fastening a fluid duct such as a fuel duct in an orifice of a turbojet casing, the device comprising a ring screwed into the orifice of the casing and having an annular rim coming to bear against a washer at the end of the duct, and a nut screwed onto the end of the duct so as to clamp the annular rim of the ring against the washer of the duct in order to fasten the duct to the casing.
    Type: Application
    Filed: April 25, 2005
    Publication date: January 26, 2006
    Applicant: SNECMA MOTEURS
    Inventors: Jacques Roche, Jacques Bunel, Frederic Ruellan, Philippe Henry
  • Rear fastening device for aircraft engine
    Patent number: 6988692
    Abstract: A rear attachment suspension or device of a turbo engine to an aircraft pylon includes an upper brace fitted with a pylon fastening device and hinged by second ball joint connections, first and second rocker bars transversal to the longitudinal axis of the engine on both sides of the axis of the engine and a third rocker bar disposed there between. The rocker bars are linked to the engine by first ball joint connections. The first and second rocker bars each include a third stand-by link and the upper brace is formed of a beam fixed rigidly to the pylon. The rocker bars are designed to ensure their interchangeability, thereby reducing the risks of error during assembly.
    Type: Grant
    Filed: May 5, 2004
    Date of Patent: January 24, 2006
    Assignee: SNECMA Moteurs
    Inventors: Félix Pasquer, Philippe Loewenstein, Marc Tesniere
  • Combustion chamber sealing ring, and a combustion chamber including such a ring
    Patent number: 6988369
    Abstract: The present invention provides a fixing or sealing ring for maximizing cooling at the end of a combustion chamber wall. For this purpose, the ring is constituted by a sleeve which is fixed around the end of a wall of the combustion chamber by means of a plurality of orifices for receiving fasteners or by means of any other system for connecting the ring to the wall. The sleeve includes at least one recess in its face facing the wall of the combustion chamber, thereby reducing the area of the sleeve that presses against the wall, and co-operating with said wall to form an open cavity in which a cooling air stream can flow.
    Type: Grant
    Filed: June 12, 2003
    Date of Patent: January 24, 2006
    Assignees: SNECMA Propulsion Solide, SNECMA Moteurs
    Inventors: Eric Conete, Francis Mirambeau, Georges Habarou, Didier Hernandez, Christophe Pieussergues
  • Friction plug welding method, for a hole in a metal part, use of a metal bar and of a bearing supporting part for implementing the method
    Publication number: 20060011708
    Abstract: The invention concerns a friction plug welding method, for a hole, extending globally along an axis, in a metal part, failing any clearance space in the axis of the hole, because of at least one obstacle on said axis, wherein a metal bar, extending globally along an axis, is rotated around its axis and is inserted into the hole, to be friction welded therein. The method of the invention is characterised in that the axis if the bar is tilted with respect to the axis of the hole of a non-zero angle (?) to avoid the obstacle. Thus, thanks to the method of the invention, it is possible to reach holes difficult of access, while orienting the axis of the bar suitably.
    Type: Application
    Filed: April 25, 2005
    Publication date: January 19, 2006
    Applicants: SNECMA MOTEURS, SNECMA SERVICES
    Inventors: Bernard Bouet, Jean-Pierre Ferte, Olivier Gourbesville, Didier Le Saunier
  • Mounting a turbine nozzle on a combustion chamber having CMC walls in a gas turbine
    Publication number: 20060010879
    Abstract: The gas turbine comprises an annular combustion chamber having inner and outer walls made of ceramic matrix composite material, and a high pressure turbine nozzle secured to a downstream end of the combustion chamber and comprising a plurality of stationary airfoils extending between the inner and outer walls of an annular flow path through the nozzle for the gas stream coming from the combustion chamber. The turbine nozzle is made of ceramic matrix composite material and it is connected to the downstream end of the combustion chamber by brazing.
    Type: Application
    Filed: June 16, 2005
    Publication date: January 19, 2006
    Applicant: SNECMA MOTEURS
    Inventors: Caroline Aumont, Eric Conete, Mario De Sousa, Didier Hernandez, Georges Habarou
  • Turbomachine nozzle cover for reducing jet noise
    Publication number: 20060010853
    Abstract: A cowl for a turbomachine nozzle, the cowl having a plurality of repeated patterns disposed circumferentially at a trailing edge, each pattern being asymmetrical about a midplane of the pattern containing a longitudinal axis of the cowl, and each pattern having a first portion inclined radially towards the inside of the cowl and a second portion inclined radially towards the outside of the cowl.
    Type: Application
    Filed: July 12, 2005
    Publication date: January 19, 2006
    Applicant: Snecma Moteurs
    Inventors: Marius Goutines, Jacques Julliard, Pierre Loheac, Frederic Miroudot, Jean-Michel Nogues, Stephane Thomas
  • Suspension part of a turbojet engine
    Patent number: 6986482
    Abstract: A suspension part for mounting a turbojet engine includes two ends equipped with two elements, juxtaposed in a widthwise direction of the suspension part, for fixing the suspension part to the fixed structure. The ends are shaped into pairs of yokes respectively flanking connecting rods and each including fixing elements and a bearing of a journal of a connecting rod which bearing is situated underneath a fixing element. The suspension part also includes slots passing through the two ends of the suspension part and running between the yokes without running over a central portion of the suspension part. Each of the yokes has an upper portion with an additional thickness located on an inside of each of the yokes.
    Type: Grant
    Filed: December 20, 2001
    Date of Patent: January 17, 2006
    Assignee: Snecma Moteurs
    Inventors: François Brefort, Lydie Chevalier, Jean-Louis Picard, Jean-Claude Félix Pasquer
  • Installation for shaping a hollow blade
    Publication number: 20060005594
    Abstract: A hollow blade is shaped by superplastic inflation of a blank made up of welded-together sheets. A die comprising two hollow shapes clamping the outline of the blank is placed inside an autoclave-forming enclosure in order to subject the blank to superplastic inflation, and the two hollow shapes are united by U-shaped clamps made of a material having a coefficient of thermal expansion that is smaller than that of the material constituting said shapes.
    Type: Application
    Filed: June 9, 2005
    Publication date: January 12, 2006
    Applicant: SNECMA MOTEURS
    Inventors: Jean-Michel Franchet, Patrick Gesmier, Benoit Marty
  • Aircraft engine with means of suspension from the structure of an aircraft
    Publication number: 20060000944
    Abstract: This invention relates to an aircraft engine comprising means of suspension from an aircraft structure with means of transmitting forces between the engine casing and the aircraft structure, and a fail safe means. The engine is characterised by the fact that the said fail safe means includes an assembly of a safety clevis with two lugs and a tab or other equivalent means arranged between the two lugs, either the clevis or the tab being fixed to an element of the engine casing and the other tab or clevis being fixed to the said structure, a safety hinge pin previously fixed perpendicular to the axis of the engine passing through the tab and the clevis, the two lugs and the tab being parallel to the engine axis.
    Type: Application
    Filed: April 28, 2005
    Publication date: January 5, 2006
    Applicant: SNECMA MOTEURS
    Inventor: Sebastien Dron
  • Blade for a turbine comprising a cooling air deflector
    Patent number: 6981845
    Abstract: The invention relates to a blade for a turbine, the blade being fitted with a dovetail root to fix it into a compartment of a turbine disk, the blade being fitted with an internal air cooling circuit comprising air inlets located on the blade dovetail root and facing the compartment, and air outlets. The blade dovetail root is fitted with a device capable of homogenising the pressure and temperature of cooling air entering the air inlets.
    Type: Grant
    Filed: April 17, 2002
    Date of Patent: January 3, 2006
    Assignee: Snecma Moteurs
    Inventors: Morgan Lionel Balland, Sylvie Coulon
  • Aircraft braking method and ducted fan jet engine for implementing the method
    Publication number: 20050279081
    Abstract: The braking method for an aircraft propelled by at least one ducted fan jet engine, the latter comprising a fan, a jet engine core in which the primary flow circulates, a secondary flow exhaust nozzle, encased in a nacelle, comprises the step, in low-power operation, of unloading at least part of the secondary flow so as to reduce the residual thrust of the jet engine without producing any thrust. With the method of the invention, aircraft braking can be achieved without any thrust reverser device using the braking force generated by the drag of the jet engine or engines completed by reduction of residual thrust by unloading the secondary flow.
    Type: Application
    Filed: June 20, 2005
    Publication date: December 22, 2005
    Applicant: SNECMA MOTEURS
    Inventor: Alain Lardellier
  • Process for manufacturing a reinforcing leading or trailing edge for a fan blade
    Publication number: 20050278950
    Abstract: A process for manufacturing reinforcing parts (14) for leading edges (10) and/or trailing edges (12) of fan blades (1) is described. In particular, this invention relates to the use of the SPF/DB (<<Super Plastic Forming/Diffusion Bonding >>) process for this type of non-hollow part.
    Type: Application
    Filed: March 4, 2005
    Publication date: December 22, 2005
    Applicant: SNECMA MOTEURS
    Inventors: Jean-Louis Despreaux, Jean-Michel Franchet, Philippe Joffroy, Gilles Klein, Stephane Leveque, Daniel Lhomme, Alain Lorieux
  • Ventilation channels in an afterburner chamber confluence sheet
    Patent number: 6976361
    Abstract: The invention relates to ventilating the confluence sheet of an afterburner chamber of an aviation turbomachine, including, upstream from the afterburner chamber: a diffuser defined by a confluence sheet disposed inside a casing, said casing and said confluence sheet defining between them an annular channel for a cold secondary flow, upstream fuel injectors being disposed at the inlet to said diffuser and flame-catchers being disposed downstream from said upstream injectors, said confluence sheet presenting, between the radial plane containing said upstream injectors and the radial plane situated at the rear ends of said flame-catchers two bends so as to flare downstream in order to slow down the primary flow F1 downstream from said upstream injectors.
    Type: Grant
    Filed: June 22, 2004
    Date of Patent: December 20, 2005
    Assignee: Snecma Moteurs
    Inventors: Thierry Cortes, Alain Page, Sébastien Baboeuf, Jacques Roche
  • Reducing clearance in a gas turbine
    Patent number: 6976824
    Abstract: A gas turbine, in particular a high pressure turbine for an airplane engine, the turbine comprising moving blades (10) with tips that are fitted with radially slidable stubs (26) for being pressed in operation by centrifugal forces against the inside surface of the casing (16) of the turbine in order to eliminate radial clearance between said surface and the tips of the blades (10).
    Type: Grant
    Filed: April 16, 2004
    Date of Patent: December 20, 2005
    Assignee: Snecma Moteurs
    Inventor: Claude Nottin
  • Turbomachine with means for axial retention of the rotor
    Publication number: 20050276683
    Abstract: The turbomachine of the invention extends longitudinally along an axis, and includes a rotor attached to drive shaft, arranged to rotate around an axis, supported by at least a first bearing, mounted on the fixed structure of the turbomachine by a bearing support element. The turbomachine is characterised by the fact that it includes a stop ring, mounted on the fixed structure of the turbomachine, to cooperate with the support element of the first bearing and, in the event of displacement of the rotor in relation to the fixed structure, to perform a function of axial retention of the rotor in an even manner, with no angle effect between the axis of the turbomachine and the axis of the drive shaft.
    Type: Application
    Filed: June 10, 2005
    Publication date: December 15, 2005
    Applicant: SNECMA MOTEURS
    Inventors: Guy Lapergue, Regis Servant, Gael Bouchy, Alain Baum
  • Inter-vane platform with lateral deflection for a vane support of a turbine engine
    Publication number: 20050276691
    Abstract: An inter-vane platform (3), for a vane support disk (1) of a turbine engine fan, comprises a central part (5) of one piece with the support disk (1) between two adjacent vanes (2), and two lateral parts (8,9), forming extensions to two lateral edges (6,7) of the central part (5), and each designed in such a way as to deflect under the impact of the vane (2) opposite which it is located.
    Type: Application
    Filed: July 19, 2004
    Publication date: December 15, 2005
    Applicant: SNECMA MOTEURS
    Inventors: Michele Queriault, Claude Lejars
  • Lightened interblade platform for a turbojet blade support disc
    Publication number: 20050276692
    Abstract: An interblade platform (3) for a blade support disc (1) on a turbojet blower comprises a deflecting part (4) comprising a lower face (5) provided with a first fixing lug (6) provided with a first orifice (7) for the passage of a first fixing stud (8) and a second fixing lug (9) provided with second (10) and third (11) orifices for the passage of second (12) and third (13) fixing studs. The fixing studs (8, 12, 13) are intended to fix the two fixing lugs (6, 9) to the support disc (1) between two adjacent blades (2).
    Type: Application
    Filed: July 19, 2004
    Publication date: December 15, 2005
    Applicant: SNECMA MOTEURS
    Inventors: Michele Queriault, Claude Lejars
  • Installation for non-destructive inspection of a part
    Publication number: 20050274188
    Abstract: An installation for non-destructive inspection makes use simultaneously of sensors responsive to different physical characteristics. In an example, a sensor support, e.g. a kind of carriage having running wheels via which it comes into contact with the surface to be inspected, is fitted with two types of sensor, namely an eddy current sensor and at least one ultrasound sensor.
    Type: Application
    Filed: June 3, 2005
    Publication date: December 15, 2005
    Applicant: SNECMA MOTEURS
    Inventors: Patrick Cabanis, Richard Coulette, Christian Marceau