Patents Assigned to SNECMA
  • Method of producing a circular fibre-reinforced metal article, and apparatus for use in said method
    Patent number: 5642851
    Abstract: An apparatus for producing a circular metal article reinforced by fibres in selected parts of its cross-section is described in which a metal blank of the article is formed and provided with at least one annular groove opening in the axial direction, preforms of reinforcing fibre and filler metal are placed in the groove which is then closed by a metal plug, and the assembly is isothermally forged to produce the article in a single forging step which serves to compress the preforms, weld the assembly together, and shape the article. Such articles may be used for machining high performance rotors for turbojet engines.
    Type: Grant
    Filed: March 20, 1996
    Date of Patent: July 1, 1997
    Assignee: Societe Nationale D'Etude et de Construction de Moteurs D'Aviation "Snecma"
    Inventors: Jean-Claude Berthelemy, Gilles Jean-Michel Bessenay, Gerard Philippe Gauthier, Daniel Georges Girault, Ludovic Edmond Camille Molliex
  • Device for assembling a circular stage of pivoting vanes
    Patent number: 5636968
    Abstract: A device for assembling a circular stage of pivoting vanes and composed of a ring for retaining bushes in which the pivots of the vanes rotate. The ring is composed of sectors extending between the pivots and connected together by a circular rail. A further ring separate from the rail or integrated with the latter is engaged in throats of the pivots so as to retain them against an axial movement.
    Type: Grant
    Filed: July 27, 1995
    Date of Patent: June 10, 1997
    Assignee: Societe Nationale D'Etude et de Construction de Moteurs D'Aviation "Snecma"
    Inventors: Jacques R. Audet, Jean-Louis Charbonnel, Gerard G. Miraucourt, Jean-Claude Prato
  • Process for manufacturing a hollow blade for a turbo-machine
    Patent number: 5636440
    Abstract: A process for manufacturing a hollow turbo-machine blade comprises the steps of:(a) using computer aided design and manufacture (CAD/CAM) means to create, from a definition of the blade to be produced, a digital simulation of the flat form of the primary parts of said blade;(b) die-forging said primary parts in a press observing certain conditions;(c) machining said primary parts;(d) depositing diffusion barriers on at least one of said primary parts according to a predefined pattern;(e) assembling said primary parts, followed by diffusion welding them together under isostatic pressure;(f) inflating the welded assembly and shaping it by superplastic forming; and,(g) final machining;the process possibly also including an additional step of cambering and twisting the primary parts either before or after they are welded together.
    Type: Grant
    Filed: August 30, 1995
    Date of Patent: June 10, 1997
    Assignee: Societe Nationale d'Etude et de Construction de Moteurs d'Aviation "Snecma"
    Inventors: Matthieu Bichon, Charles J. P. Douguet, Alain G. H. Lorieux, Yvon M. J. Louesdon, Florence A. N. Renou
  • Composite material turbine engine blade equipped with a seal and its production process
    Patent number: 5628622
    Abstract: A turbine engine blade made from a composite material and having at a free end thereof an integrated brush joint. A process for producing such a blade includes the steps of:introducing a fibrous fabric into a mold,introducing specific fibres into the mold, in the vicinity of the free end of the blade,injecting a resin into the mold,performing polymerization by use of a heating press of the resin-impregnated fibrous fabric.
    Type: Grant
    Filed: August 23, 1995
    Date of Patent: May 13, 1997
    Assignee: Societe Nationale d'Etude et de Construction de Moteurs d'Aviation "Snecma"
    Inventors: Monique A. Thore, Pascal C. M. A. Vasseur
  • Turbojet equipped with a deicing system on the intake case
    Patent number: 5623821
    Abstract: A turbojet having an air intake case including radial arms between an outer annular structure and an inner central structure, and a deicing unit configured to deice the radial arms by microwaves and located in the central structure. The deicing unit has a microwave generator and a transmitting element configured to transmit energy and including an inside annular waveguide located inside of the central structure. An energy distributing element configured to eliminate ice is coupled with the transmitting element by a coupling element. The radial arms are made from a dielectric composite material.
    Type: Grant
    Filed: July 31, 1995
    Date of Patent: April 29, 1997
    Assignee: Societe Nationale d'Etude et de Construction de Moteurs d'Aviation "Snecma"
    Inventors: Philippe Bouiller, Claude G. Corbin, Michel Franchet, Gerard E. A. Jourdain
  • Axial fixing arrangement for rotor blades of a turbomachine
    Patent number: 5622476
    Abstract: A fixing arrangement for axially fixing a blade in position on a rotor disk of a turbomachine rotor includes a relatively flexible locking wedge inserted between the root of the blade and the bottom of the axial groove in the periphery of the rotor disk in which the root is received in a radially interlocking manner, the locking wedge having a retaining hook which is received in a groove in the blade root to hold the locking wedge in position. In one embodiment the locking wedge holds a plate in position in the recesses defined by undercut projections on the upstream face of the blade root and the rotor disk to prevent axial movement the blade relative to the disk.
    Type: Grant
    Filed: December 14, 1995
    Date of Patent: April 22, 1997
    Assignee: Societe Nationale d'Etude et de Construction de Moteurs d'Aviation "SNECMA"
    Inventors: Danielle C. R. Adde, Jean-Louis Charbonnel, Philippe F. P. Gougeon, Gerard G. Miraucourt
  • Turbine engine equipped with means for controlling the play between the rotor and stator
    Patent number: 5616003
    Abstract: A turbine engine includes a ferrule formed of a plurality of ferrule elements in the shape of circular sectors, each bearing on one internal face thereof fixed vanes and a circular housing surrounding the ferrule. The turbine has a support ring including a plurality of circular ring sectors each secured to the housing and having a U-shaped section whose opening is directed towards the ferrule, each ferrule element includes a hooking mechanism (9a) to be introduced into the opening of at least one ring sector so as to integrally connect the ring sector and the ferrule element.
    Type: Grant
    Filed: October 26, 1994
    Date of Patent: April 1, 1997
    Assignee: Societe Nationale d'Etude et de Construction de Moteurs d'Aviation "SNECMA"
    Inventors: Jean-Louis Charbonnel, Daniel J. Marey, Fabrice Marois, Gerard G. Miraucourt
  • Non-destructive process for characterizing the surface condition of a part
    Patent number: 5610326
    Abstract: A process for checking the surface condition of a part, particularly in areas which are difficult to access, comprises making a rough preliminary imprint of the surface using an elastomeric material of medium precision in paste form and allowing the material to harden so that the preliminary imprint forms a supporting mold, casting a high precision elastomeric material, preferably in silicone based material, into the supporting mold and applying it to the surface to form an accurate imprint which is allowed to harden and, after removal, is inspected to determine the surface condition.
    Type: Grant
    Filed: June 28, 1995
    Date of Patent: March 11, 1997
    Assignee: Societe Nationale d'Etude et de Construction de Moteurs d'Aviation "Snecma"
    Inventor: Daniel L. L. Leost
  • Turbo aero engine provided with a device for heating turbine disks on revving up
    Patent number: 5586860
    Abstract: Turbo aero engine including a heating arrangement for the internal portions (12) of turbine disks on revving up so as to reduce the temperature gradient in the disks. Heating gas passes through pipes (11) integral with the stator and reheats the disks by passing through a gasket (13) designed with the tongues (18) and orifices (20 and 22) which allow the gas to circulate towards the zones to be heated when the revving up has firstly heated the portions of the machine close to the pipes (11) and then makes it possible to interrupt the communication when the temperatures even out and the original heat expansions become uniform and offset the orifices (20 and 23).
    Type: Grant
    Filed: October 31, 1994
    Date of Patent: December 24, 1996
    Assignee: Societe Nationale d'Etude et de Construction de Moteurs d'Aviation "Snecma"
    Inventors: Jean-Louis Bertrand, Gilles A. Charier, Xavier J.A. Guyonnet, Jean-Louis Picard
  • Turbocompressor disk provided with an asymmetrical circular groove
    Patent number: 5584658
    Abstract: A turbocompressor disk having on its periphery a circular groove able to receive blade roots having a substantially hammer shape, said circular groove comprising an upstream lip and a downstream lip against which bear the blade roots. The upstream lip has a curvature of gradient inclined by an angle .alpha. with respect to the plane perpendicular to the rotation axis and the downstream lip has a curvature of gradient inclined by an angle .beta. with respect to the plane perpendicular to the rotation axis, .alpha. being strictly different from .beta..
    Type: Grant
    Filed: July 21, 1995
    Date of Patent: December 17, 1996
    Assignee: Societe Nationale d'Etude et de Construction de Moteurs d'Aviation "SNECMA"
    Inventor: Jacques M. P. Stenneler
  • System for balancing and damping a turbojet engine disk
    Patent number: 5582077
    Abstract: A rotor disk arrangement for a turbojet engine includes a balancing and damping system which has a ring having a circumferential surface recessed with housings and balance masses respectively positioned in the housings. A disk having a circumferential surface is provided which engages the circumferential surface of the ring. The circumferential surfaces are provided with a plurality of bayonet couplings, the couplings including a tenon and a groove engaged with the tenon. The groove includes a straight entrance portion which is substantially parallel to the axis of the engine and a crooked hind part which is substantially circumferentially positioned in the engine. In addition, a plurality of tongues are provided which are respectively inserted into the entrance portions of the grooves and fastened to the ring.
    Type: Grant
    Filed: February 23, 1995
    Date of Patent: December 10, 1996
    Assignee: Societe Nationale d'Etude et de Construction de Moteurs d'Aviation "Snecma"
    Inventors: Daniel A. Agram, Philippe Bodet, Fran.cedilla.ois G. Dhyser, Gerard D. Prigent
  • Redundant mass flow meter
    Patent number: 5583302
    Abstract: A redundant mass flow meter comprises a casing housing a main rotor and an ntermediate rotor which is freely rotatable and is disposed coaxially with a rotationally restricted turbine between the turbine and the casing, a first measuring system for measuring and controlling the position of the turbine relative to the intermediate rotor, and a second measuring system, independent of the first measuring system, for measuring and controlling the position of the intermediate rotor relative to the casing.
    Type: Grant
    Filed: June 23, 1995
    Date of Patent: December 10, 1996
    Assignee: Societe Nationale d'Etude et de Construction de Motors d'Aviation "Snecma"
    Inventor: Jean-Paul Perrin
  • Turbo-jet equipped with inclined balancing disks within the rotor of the high pressure compressor and process for producing such disks
    Patent number: 5579644
    Abstract: A method and apparatus for maintaining or holding the rotor of a high pressure compressor of a very rigid turbojet during turbojet operation. The interior of the rotor of the high pressure compressor comprises upstream-inclined balancing disks (13) which are free of fly-weights. The centrifugal force applied to such balancing disks creates a load or stress on the disks having a radial component rending to compensate for the stresses towards the outside due to the blades, in front of which are positioned the balancing disks. The process for the production of such an exhaust cone is made easier, particularly with respect to the blank to be supplied for obtaining such a part.
    Type: Grant
    Filed: September 30, 1994
    Date of Patent: December 3, 1996
    Assignee: Societe Nationale d'Etude et de Construction de Moteurs d'Aviation "Snecma"
    Inventor: Jacky S. Naudet
  • Metallic lip seal and turbo jet engine equipped with said seal
    Patent number: 5577887
    Abstract: The seal prevents any particles absorbed by the turbo jet engine from sliding between the upper surface of the disk (1) of the high pressure turbine and the labyrinth (2) secured to the latter.This seal includes a body (5C) placed in a cavity (6) of the labyrinth (2) and a lip (5L) resting on the upper surface (1AM) of the disk (1) so that on stopping there is a small space (6) between the labyrinth (2) and the seal (5).Application for all aircraft turbo jet engines.FIG. 2.
    Type: Grant
    Filed: June 26, 1995
    Date of Patent: November 26, 1996
    Assignee: Societe Nationale d'Etude et de Construction de Moteurs d'Aviation "Snecma"
    Inventors: Philippe A. C. Gouyon, Jerome E. R. Jolu, Gilles C. Meunier, Jacques A. A. Rauner, Patrice J.-M. Rosset
  • Process and apparatus for automatically characterizing, optimizing and checking a crack detection analysis method
    Patent number: 5570431
    Abstract: Quantitative characterization of a crack detection analysis method is achieved by determining the detection sensitivity and background noise produced by the analysis method by suitably processing images obtained from one or more control specimens prepared by the method and subjected to appropriate and optimized conditions of illumination. In addition, the crack detection analysis method is optimized by looking for the parameters which influence the method and determining the value thereof which maximizes detection sensitivity and minimizes background noise.
    Type: Grant
    Filed: October 20, 1994
    Date of Patent: October 29, 1996
    Assignee: Societe Nationale d'Etude et de Construction de Moteurs d'Aviation "Snecma"
    Inventors: Herve, P. R. Gillard, Veronique H. M. P. Prejean-Lefevre
  • Method of producing a circular fibre-reinforced metal article, and apparatus for use in said method
    Patent number: 5562245
    Abstract: A method of producing a circular metal article reinforced by fibres in selected parts of its cross-section is described in which a metal blank of the article is formed and provided with at least one annular groove opening in the axial direction, preforms of reinforcing fibre and filler metal are placed in the groove which is then closed by a metal plug, and the assembly is isothermally forged to produce the article in a single forging step which serves to compress the preforms, weld the assembly together, and shape the article. Such articles may be used for machining high performance rotors for turbojet engines. Apparatus for use in the method is also described.
    Type: Grant
    Filed: December 8, 1994
    Date of Patent: October 8, 1996
    Assignee: Societe Nationale d'Etude et de Construction de Moteurs d'Aviation "Snecma"
    Inventors: Jean-Claude Berthelemy, Gilles J. Bessenay, Gerard P. Gauthier, Daniel G. Girault, Ludovic E. C. Molliex
  • Process and apparatus for automatically characterising, optimising and checking a crack detection analysis method
    Patent number: 5563417
    Abstract: An apparatus for characterizing an analysis method based on fluorescent crack detection. The surface defects in articles to be checked are revealed by using a visible radiation around an excitation wavelength. The apparatus includes an illumination device, a camera and an image processor. The illumination device includes an ultraviolet light source, a monochromator and a light guide to focus the ultraviolet radiation.
    Type: Grant
    Filed: September 6, 1995
    Date of Patent: October 8, 1996
    Assignee: Societe Nationale d'Etude et de Construction de Moteurs d'Aviation "SNECMA"
    Inventors: Herve P. R. Gillard, Veronique H. M. P. Prejean Lefevre
  • Fixing arrangement for a thermal protection tile in a combustion chamber
    Patent number: 5560197
    Abstract: An arrangement for removably fixing a thermal protection tile on the inside of a combustion chamber wall is described. In one form the tile is provided with a fixing stud which is arranged to pass through a hole in the wall, and a split washer is inserted under the head of the stud to lock the assembly to the wall. In another form the tile is provided with a fixing stud having a head which is arranged to be inserted in a socket welded to the inner surface of the wall and which is locked in place by a stop inserted through a hole in the wall to abut the edge of the head and prevent its removal from the socket.
    Type: Grant
    Filed: September 25, 1995
    Date of Patent: October 1, 1996
    Assignee: Societe Nationale d'Etude et de Construction de Moteurs d'Aviation "Snecma"
    Inventors: Denis R. H. Ansart, Didier Hernandez, Rodolphe Martinez
  • Process for welding two blade parts
    Patent number: 5551623
    Abstract: Process for welding two blade parts (9, 10) by a means such as a linear friction welding machine, in which a collar or flange (15) of material to be sacrificed is placed between the contact surfaces (16) or around the latter in order to increase the heat produced by the friction at the leading and trailing edges of the blade. As a result of this arrangement it is possible to start with two blade parts (9, 10) having the dimensions of the finished product, possibly with the exception of the area around the contact surfaces, so that the final machining is very significantly reduced.
    Type: Grant
    Filed: February 17, 1995
    Date of Patent: September 3, 1996
    Assignee: Societe Nationale d'Etude et de Construction de Moteurs d'Aviation "SNECMA"
    Inventors: Andre C. F. Collot, Jean-Pierre Ferte, Roger Jolly
  • Adjustment valve for injecting fuel for a turbojet engine
    Patent number: 5548959
    Abstract: An adjustment valve is provided with a system able to prevent its piston from jamming. This piston (30) is fitted with a vane wheel (50) placed at its end and receiving a flow of air under pressure. The piston is thus in constant rotation inside the body (20) of the valve. Application is for the injection of fuels in turbojet engines.
    Type: Grant
    Filed: March 29, 1995
    Date of Patent: August 27, 1996
    Assignee: Societe Nationale D'Etude et de Construction de Moteurs D'Aviation "SNECMA"
    Inventor: Michel M. A. A. Lechevalier