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

General Electric Company

Hispano Suiza

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

(s.n.e.c.m.a.) Societe National D'etude Et De Construction De Moteurs

Jean-Louis Charbonnel

Jacky S Naudet

Gerard G Miraucourt

Daniel J Marey

Jean-Claude Prato

Pierre Debeneix

Yann J Rigaud

Christopher Charles Glynn

Bruno Albert Beutin

Pierre Charles Mouton

Georges Mazeaud

Roger C Walker

Michel Franchet

Jean-Claude L Delonge

Gerard Jacques Stangalini

Andre C Collot

Guy Franck Dusserre-Telmon

Monique A Thore

Gerard R Vermont

Daniel A Agram

Jean-Pierre Galivel

Jean-Paul Lagrange

Philippe Fessou

Daniel J Martin

Claude Dejaune

Michel A Bouru

Laurent Gille

Thierry J Niclot

Fabrice Marois

Thierry Henri Tassin

Christian J Cattaneo

Jean-Christophe M Cordier

Jean-Pierre A Mourlan

Gerard Receveur

Corinne Follonier

Alain M Bromann

Philippe Guerout

Jacques L Happey

Jean-Claude Porcher

Frederic G Mainfroy

Denis B Pottier

Jean-Luc C Goga

Christophe Brichet

Jacques R Audet

Jean-Francois Van De Voorde

Danielle C Adde

Philippe G Joly

Philippe F Gougeon

Jean-Francois Ranvier

Herve Paitre

Chloe Avila

Jean-Claude Gregoire

Alain Espenel

Corrine G Delahaye

Marie-Lise Dardenne

Didier M Nouveau

A gas turbine engine incorporating a starter mounted on the gear box is disclosed. The gas turbine engine includes an AGB gear housing mechanically connected with an engine shaft for driving auxiliary machines and an air starter mounted on the housing, the starter and housing enclosures being in communication such that the lubricating oil of the starter should be distributed from the AGB housing. The oil enclosure of the starter is pressurized by a source of air, being independent from the AGB housing. Advantageously, the pressurization air is taken from a pressurization enclosure of an engine bearing.

Gas turbine engine comprising a starter in the auxiliary gear box

Pivoting vane internal extremity bearing (1) whose internal extremities are connected by a linking ring (12). The bearing elements (18) connecting the internal extremity pivots (10) to the ring (12) are composed of a bush (19) prolonged by bearing necks (20) with a spin axis (X') parallel to that of the ring (12). The forces undergone by the vanes, which transversally move the pivots (10), do not cause any wear of the bush (19), but a rotation of the latter around the axis (X'). Application for turbine aero engine stator vanes.

Pivoting vane internal extremity bearing

The arrangement of a gas turbine engine suitable for high bypass ratio aircraft engines in which gases circulate in a primary air channel (7) and a secondary channel (8) concentric to said primary air channel, is characterized in that structural vanes (22) connecting the channel delimitation casings (2, 10, 14, 5) with each other, alternate with aerodynamic vanes (20) for guiding the gases on a common circumference of the engine bypass air channel (8), and in that the structural channels branch out between the two channels. The resulting advantages are simplicity of construction associated with a reduction in the space required for housing the channels and good resistance without notable increase of the total mass.

Arrangement of gas turbine engine comprising aerodynamic vanes and

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

Device for controlling pivoting blades or variable pitch blades (3) in a turbine in which the control ring (10) rotates under the effect of an angled cam (15) controlled by a system with a connecting rod (22) and crank (21). This system imposes a non-linear rotation law between the blades (3) and the crank (21).

Control device for a stage of blades with variable pitch

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.

Device for assembling a circular stage of pivoting vanes

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. In an alternative embodiment the downstream end of the locking wedge has a stop which engages the downstream faces of the blade root and the rotor disk to prevent axial movement of the blade in the upstream direction, and the upstream face of the blade root has a projection which overlaps and bears against an upstream face of the disk to prevent axial movement of the blade in the downstream direction.

Axial fixing arrangement for rotor blades of a turbomachine

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.

Turbine engine equipped with means for controlling the play between the

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

A system for retaining and sealing vanes and composed of an flange provided with a throat on tabs which are interlaced in other tabs, also provided with throats of the vane feet. An elastic joint is engaged in the throats and a disk throat and keeps the elements of the flange and the vanes in an axial position.

Retaining and sealing system for rotor blades

A removable inspection hole plug for sealing a plurality of inspection holes formed in a double-walled enclosure is disclosed in which individual sealing units are disposed in each of the inspection holes, with the individual sealing units linked together by a link rod pivotally attached to each of the sealing units. A seal is provided on each of the sealing units which slideably engages a wall defining the inspection hole and the link rod may be attached to the sealing units by a ball and socket swivel joint. One of the sealing units is attached to a housing which is, in turn, removably attached to the enclosure such that the sealing unit may undergo limited axial movement relative to the housing. This accommodates differential thermal expansion between the walls of the enclosures and also facilitates removal of the inspection hole plug by merely unfastening the housing from the enclosure and removing the housing along with the sealing units.

Removable inspection hole plug

Variable phase vane provided with a composite pivot having a joining piece for receiving the control pieces. The joining piece is made of a material less dense than the actual pivot. These two elements are force-fitted without using any weld or mechanical linking device. The vane finally obtained is thus rendered lighter in weight

Variable phase vane

An annular gasket includes, at least partially conically shaped portion and is supported on a rotor via three bearing surfaces. The conical shape makes it possible to reject the center of gravity of the sections of the rotor which provokes substantial rotational movement when centrifugal forces exist and allows for an improved imperviousness via the internal and external bearings. This invention is applicable for the rotors of aircraft engines provided with axial broachings in which blade feet are able to slide.

Annular gasket disposed at one axial extremity of a rotor and covering

A device for ensuring the sealing in a rotary machine between a rotor and fixed blade stages. Blade edges are joined by rings carrying circular seals in slots. Springs force the seals in the longitudinal direction towards transverse faces of reinforcements of the rotor. A turbulence-free gas flow is obtained as a result of the total seal obtained by the seals (19). Moreover, the rotor can be constructed with a substantially rectilinear ferrule which only induces limited stress concentrations.

Sealing device between blade stages and a rotary drum, particularly for

A sealing structure for a gas turbine blade which pivots about a pivot shaft. A split ring is located in a groove on the shaft, in which the ring can be embedded and held by a bush. When the blade is fitted, the bush abuts against a wall of the stator, slides on the pivot shaft and frees the ring, which expands and forms the seal. The invention relates to gas turbines where the stator blades have a variable setting.

Sealing structure for a pivoting blade of a gas turbine

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Boissise le Roi, France

Jean-Louis Charbonnel