Snecma

Snecma Moteurs

Safran Aircraft Engines

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

Dominique Raulin

Fabrice Marois

Thierry Georges Paul Papin

Sebastien Juste

Gabriel Radeljak

Alain Jean Chatel

Romain Nicolas Lunel

Jacky S Naudet

Gerard E Jourdain

Christophe Pieussergues

Antoine Robert Alain Brunet

Gilles Pierre-Marie Notarianni

Jérémy Guivarc'h

Alain Chatel

Emmanuel Houradou

Bruno Dambrine

Thibault Ruf

Benjamin Frantz Karl Villenave

Frédéric Brettes

Frédéric Jean-Bernard Pouzadoux

Ollivier Carletti

Lise Lacroix

Claude J Loudet

Thierry Francois Maurice Duchatelle

Francois Pierre Georges Maurice Ribassin

Philippe Jean-Pierre Pabion

Dan Ranjiv Joory

Arnaud Sanchez

Jeremy Guivarc'h

Patrick Edmond Kapala

Alain François Jean Lavie

Gerard Francedillaois Inizan

Patrick Kapala

Francois M Marlin

Christine J Ruffier

Damien Bonnefoi

Alain Raffy

Julien Sedlak

Frederic Jean-Bernard Pouzadoux

Jeremy Guivarc'H

Frédéric Renault

Pierre Savoyat

Jean-Paul Bourgeois

Laurence Prato

François Marlin

Régis Servant

Thierry G Pancou

Luc Namer

Lucien Pham

Eric Lippinois

Thierry François Maurice Duchatelle

Christophe Charon

Gra&euml;me Cook

Antoine Brunet

Frederic Renault

Herve Hulin

Alain Jean Charles Chatel

Claude Chomel

Pierre Yves Bailleul

Sebastien Goux

Rene Lefloch

Patrice Mazzotta

Michel San Basilio

Florent Raine

Serge Bongrand

Alain Henri Daniel Bouron

Sébastien Georges Roger Goux

Alain Bouron

Gr&eacute;gory Garcia

Alain Repussard

François Ribassin

Hervé Hulin

Sébastien Juste

Sebastien Georges Goux

Claude Loudet

Graeme Cook

Gregory Garcia

Thierry Georges Papin

Thierry Francois Duchatelle

Alain Henri Bouron

The invention concerns a turbo engine comprising a combustion chamber () arranged inside the outer housing () and comprising an internal revolution wall () and an external revolution wall (). First stop parts () and second stop parts () fixed respectively to the outer housing and to the combustion chamber are provided, the first and second stop parts being adapted to come to a substantially axial stop two by two by forming stop pairs ().

Combustion module for a gas turbo engine with chamber bottom stop

A blade including a blade body made of organic matrix composite material and a leading edge shield made of a material that withstands point impacts better than the composite material of the blade body. The blade includes a blade tip. The leading edge shield is assembled on the blade body and includes a pressure-side fin and a suction-side fin. The pressure-side fin includes a pressure-side tab and the suction-side fin includes a suction-side tab, the pressure-side tab and the suction-side tab are folded one on the other and being secured to each other so as to form a partial covering of the blade tip. A turbojet includes a fan including such blades, and also a method of fabricating such a blade.

Blade comprising a folded leading edge shield and method of manufacturing the blade

An assembly () comprising a core () and at least a first sheet () held on one side of the core by a rivet (), the rivet having two ends (). At least a first one of these ends () is flared in shape and extends at least through the entire thickness of the first sheet (). A method of fabricating such an assembly, in which: a core () and a first sheet () are provided; the first sheet () is placed on one side of the core (); and the core () and the first sheet () are riveted together.

Riveted assembly and associated production method

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.

Hydraulic device for changing the pitch of a propeller

A plate closes the main part of a vane in two parts. An internal cavity is closed by the plate. Around a bearing surface of the plate, a groove receives an elastic seal, and the outer edge of the plate extends over the groove to compress the seal and to establish excellent leak proofing. The position of the plate may be guaranteed by centring pins penetrating into holes adjacent to the seal and which it fills when the pins have been removed, which completes the closing of the cavity. The plate has application in particular to stationary gas guide vanes in turbine engines.

Turbine engine vane plate seal

A structural and aerodynamic module including two blades each extending along a longitudinal axis, in which each blade includes a leading edge, a trailing edge, a radially inner edge, and a radially outer edge, is provided. The module also includes a radially inner platform mechanically connecting the radially inner edges of the two blades, and a radially outer platform mechanically connecting the radially outer edges of the two blades such that the two blades and the radially outer and inner platforms delimit a flow stream. The two blades and the platforms are made from a composite material and the two blades are fixed on the radially outer and inner platforms using screw-nut assemblies.

Structural and aerodynamic module for a turbomachine casing and casing structure comprising a plurality of such a module

A structural frame for a turbomachine, such as an intermediate frame or an exhaust frame, the frame including at least two coaxial rings, an inner ring and an outer ring, together with radial arms interconnecting the rings. At least one of these elements includes a plurality of parts that are fastened together by bolting.

Structural frame for a turbomachine

The invention relates to a turbomachine module comprising a device to improve radial clearances, comprising an outer casing (), an inner casing () and at least one shock absorbing ring () connecting the casings, the module also comprising an annular cavity () on the downstream side of the ring (), with a passage () formed in it through which an airflow () is drawn off from the primary flow (Fp). According to the invention, the device to improve radial clearances comprises a thermal inertia control device for the shock absorbing ring mounted on the shock absorbing ring (), downstream from it, this device comprising at least one coat of thermal insulation (), and at least partly delimiting the annular cavity () on the downstream side of it ().

Turbomachine module provided with a device to improve radial clearances

A bearing for a turbomachine variable pitch stator vane pivot mounted in a bore of the turbomachine casing is disclosed. The bearing includes an inner bushing secured to the pivot and an outer bushing secured to the bore. An elastomeric material is inserted between the inner bushing and the outer bushing to allow the vane to pivot about its axis and absorb at least some of the flexing of the pivot at right angles to the axis. The design makes it possible to reduce bearing bushing wear.

Bearing for variable pitch stator vane

A device for controlling variable-pitch vanes in a turbomachine has rods each having at one end a finger for mounting in a control ring and at its other end an assembly orifice for mounting on a drive square of a vane, the axis of the vane being inclined relative to the axis of the finger of the rod, and the assembly orifice in the rod presenting a dimension in the longitudinal direction of the rod that is greater than that of the drive square, and co-operating therewith to define clearance that varies over the height of the drive square and of the orifice.

Device for controlling variable-pitch vanes in a turbomachine

The manufacturing cost of the control device is relatively low. This device comprises mainly a first end () of a control lever () provided with a drive hole () that drives the driving part () of a blade () through a first contact area (). The close contact between these two parts in this area is obtained using a play compensation plate () bearing on a side part () of the control lever (), and fixed to the assembly using a nut () screwed onto the external pivot () of the blade (). For application on turbomachines.

Control lever attachment with play compensation for blades with variable setting angles

A machine stator and assembly and disassembly methods. The elements of a casing portion are formed of consecutive shells in line with grooves configured to house roots of guide vane stages that are fixed in place by springs and pins for stopping rotation. The elements are arranged in a complete circle, and the assembly is made by axially separating the elements to insert the guide vane stages between the elements by a radial movement.

Machine stator and mounting and dismounting methods

The pitch control mechanism (controlling the angular position) for stator blades in a turbojet may be adjusted separately for two adjacent stages of blades controlled by a common actuatorTo achieve this, the synchronization barlocated between the mechanisms leading to the two stages is inclined, this inclination being determined by a pinand grooveconnection with the casing, while another pinand grooveconnection is arranged between the synchronization barand one of the mechanisms. Strongly non-linear displacement laws between the two mechanisms may thus be controlled depending on the shapes and directions of the grooves.

Variable pitch device for two blade stages fixed onto a turbojet

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 device for controlling variable-pitch vanes in a turbomachine comprises links connecting the radial pivots of the vanes to radial fingers carried by semicircular elements and bridges of a control ring, the links being mounted in ball-and-socket manner on the radial fingers which are fixed to the control ring. This form of mounting enables all the vanes associated with the control ring to be set to the same angular pitch.

Growing community of inventors

Saint Fargeau Ponthierry, France

Dominique Raulin