Societe Nationale D'etude Et De Construction De Moteurs D'aviation

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General Electric Company

Jacky S Naudet

Jean-Louis Charbonnel

Gerard G Miraucourt

Jacques M Stenneler

Pierre Debeneix

Daniel J Marey

Philippe P Catte

Yann J Rigaud

Christopher Charles Glynn

Roger C Walker

Dominique Raulin

Michel Franchet

Daniel Germain Kettler

Claude R Lejars

Didier Georges Feder

Jean-Claude L Delonge

Jean-Max M Silhouette

Guy Franck Dusserre-Telmon

Guy Jean-Louis Lapergue

Fabrice Marois

Gerard Jacques Stangalini

Daniel A Agram

Bertrand Pierre Renaud Monville

Jean-Pierre Galivel

Gerard Etoile

Jean-Claude Prato

Patrice Suet

Laurent Claude Patrick Salperwyck

Gerard R Vermont

Laurent Gille

Jean-Christophe M Cordier

Thierry J Niclot

Jean-Louis Bertrand

Thierry Henri Tassin

Carmen Miraucourt

Gabriel Radeljak

Marc Berthillier

Jean-Pierre Caubet

Antoine Jean

Alain Henri Daniel Bouron

Pascal G&eacute;rard Gervais

Alain M Bromann

Serge Bongrand

Philippe Guerout

Jacques L Happey

Jean-Claude Porcher

Frederic G Mainfroy

Denis B Pottier

Jean-Luc C Goga

Frederic Babec

Christophe Poy

Gael Gaignon

Jean Claude Boudot

Aude Rivory

Jean-Pierre A Mourlan

Jacques Leveaux

Pascal Michel Daniel Lejeune

Monique Andr&eacute;e Thore

Jean-Luc Christian Yvon Goga

Jean-Luc Mary

Philippe Chereau

Michel A Brioude

Andr&eacute; Collot

Christophe Brichet

Jean-Francois Van De Voorde

Philippe G Joly

Gabrijel Radeljak

Corrine G Delahaye

S&eacute;bastien Riccioz

Sébastien Georges Roger Goux

Didier M Nouveau

Gerard Receveur

Alain Henri Bouron

Sebastien Georges Goux

Andre Collot

Marc J Berthillier

André C Collot

Jean-Luc A Mary

A device for positioning and maintaining electric harnesses on the casing of a turbo-jet engine includes harness supports standardized for directions substantially perpendicular to the axis of the turbojet engine and harness supports standardized for directions substantially parallel to the axis of the turbo-jet engine.

Device for maintaining and positioning harnesses on a turbo-jet engine

A rigid link of adjustable length includes a yoke with a transversal stud. The stud is mounted on the yoke with two bearings, each inside a through-orifice in the yoke. The axis of the stud is offset from the axis of the bearings whereby the link includes a stopping device in order to lock the stud in at least two different positions, relative to the yoke.

Link between two mechanical members

A device for stopping rotation of a fixed blade bearing sector in a gas turbine casing. Sectors of synchronizing ring blades are maintained against tangential rotational movements by sliding into grooves of a casing by pins passing through perforations in an extension of the two parts. The pins are prevented from accidental removal either by a flexible lock ring or by a locking tab maintained between the two parts when they have been completely assembled.

Device for stopping in rotation a fixed blade bearing sector in a gas turbine casing

A flexible rod ( ) is articulated at a first end to a control ring ( ) and is fixed at a second end to a pivot of a blade ( ) that is to be controlled. At this second end, it is held so that it can rotate without play on the blade pivot by a holding device ( ). The articulation device comprise a pivot ( ) passing through a first orifice ( ) pierced in this first end and engaged in a radial housing ( ) of the control ring, the pivot being held in position by a locking ring ( ) which has openings ( ) for the passage of this pivot and which slides on this control ring. The fixing device comprise a fixing screw ( ) passing through a second orifice ( ) pierced in the second end of the rod and introduced into a hole ( ) of the pivot of the blade that is to be controlled.

Device for controlling variable-pitch blades

These objects are achieved by a method of acoustically inspecting a one-piece bladed wheel in which the wheel is driven in rotation; each blade of the wheel is subjected to mechanical excitation; its acoustic response is picked up and a corresponding electrical signal is generated; its frequency response is determined by computing a FFT; the electrical signal and the associated frequency response are stored; the characteristic frequencies of each blade of the wheel are identified; and a wheel is rejected or accepted depending on whether or not the frequency distribution obtained in this way matches a predetermined set of forbidden frequency distributions. Advantageously, an additional step is provided in which the defects of a blade are determined by comparing its frequency response with predetermined frequency responses that are characteristic of various types of defect.

Acoustic inspection of one-piece bladed wheels

The invention relates to hammer-fastener blade-locking device affixing the blades in the channel ( ) of a turbojet-engine rotor disk ( ) and comprising a case ( ) of which the cross-section matches that of the channel ( ), further a locking element ( ) mounted in radially displaceable manner in a traverse orifice in the case ( ) and receivable in part in a lock housing ( ), and a drive bolt ( ) acting on the locking element ( ). The locking element ( ) comprises stops ( ) sliding in windows ( ) of the case ( ). The bolthead ( ) is large and is radially affixed between the bottom of the channel ( ) and the base ( ) of the case ( ).

Blade locking device with hammer fastener on a disk

A stator suitable for high-pressure compressors in gas turbine engines includes two points of ventilation at different temperatures. It is recommended that the upstream section of the stator be constructed with a casing and a shroud, both of which are unbroken around a circumference and made of a material with a low degree of thermal expansion. Downstream the shroud is, however, constructed using angular sectors in a material with a higher degree of thermal expansion.

High-pressure compressor stator

An axisymmetric, converging-diverging turbojet-engine exhaust nozzle for jet deflection. The diverging flaps are connected by linkrods to a vectoring ring ( ). The vectoring ring ( ) is driven by linear actuators ( ) anchored in the stationary structure ( ). The linear actuators ( ) are connected by a swivel ( ) to the vectoring ring ( ) and are affixed to the stationary structure ( ) to absorb the tangential loads applied by the exhaust gases on the diverging flaps and to allow positioning the vectoring ring ( ). Preferably the linear actuator ( ) is connected by a sheath ( ) to the vectoring ring ( ), the sheath ( ) slidable on the actuator case ( ) and being displaceable in a radial plane passing through the turbojet-engine's axis.

Axisymmetric, converging-diverging, jet-deflecting turbojet-engine exhaust-nozzle

A leaktight seal includes plaquettes that are housed between platforms of &ldquo;hammer legged&rdquo; vanes and a periphery of a rotor disc. The plaquettes lie above a throat that receives legs between a collar. The plaquettes are completed with heels that also lie between the legs. Centrifugal forces distort the seal and produce excellent leaktightness between the disc and the platforms.

Leaktight seal of a circular vane stage

A system for inspecting internal zones of a machine, such as an engine, comprises an observation device having an optical fiber endoscope, and distribution and guide means including a network of flexible guide sheaths placed in the machine to define a number of different inspection routes along which the endoscope can be guided from an aperture in the machine wall to various predetermined critical internal zones. Preferably the system includes first electrical means implanted in each guide sheath and co-operable with second electrical means secured to the endoscope in order to detect the position thereof in the network and to transmit the position to a monitoring device outside the machine for monitoring and assisting the guidance of the endoscope in the network.

System for inspecting internal zones of a machine by optical fibre

The blades (10) of a turbine or a compressor are here fixed to the disk (1) by three roots (7, 8 and 9) inserted in the same number of circular grooves (4, 5 and 6). This assembly makes it possible to provide a good distribution of stresses during functioning.

Bladed disk with three-root blades

Screw or nut braking rings and mountings established with the rings include a nut having an upper portion hollowed from a circular throat. Slits divide the upper portion into blocks by cutting the throat. A shape-memory alloy ring is housed in the throat so as to retighten the blocks on the threaded portion of the mounting and thus tighten it. The ring exhibits a change between the tightening state and a mounting state where it is free in the throat and can be easily mounted.

Braking nuts or screws and mountings obtained with same devices

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.

Turbo-jet equipped with inclined balancing disks within the rotor of the

Turbojet engine compressor . . . Its rotor (43) includes a movable end portion (45), such as a monoblock vaned disk able to be removed and replaced by a block. High and low pressure shaft lines (54) are formed into several portions to enable these operations to take place without having to dismantle the entire engine.

Compressor turbojet engine whose rotor has a movable upstream stage

A turbine engine stator has a metal casing surrounding an envelope carrying bearings for the pivots of pivoting blades. A control mechanism for setting the position of the blades includes a radial spindle to which are transmitted the thrust forces of the gases, the envelope being advantageously formed from angular sectors of axially juxtaposed flanges or rings and which are not loaded. Therefore, the bearings are not subject to wear giving rise to gas leaks and efficiency losses. Advantageously, the envelope is made from a composite material.

Turbine engine stator with pivoting blades and control ring

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Bondoufle, France

Jacky S Naudet