Safran Aircraft Engines

Snecma

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

Snecma Moteurs

Snecma Propulsion Solide

Safran

Safran Ceramics

Bruno Dambrine

Dominique Coupe

Ludovic Edmond Molliex

Eric Bouillon

Matthieu Arnaud Gimat

Yann Marchal

Jean-Noel Mahieu

Olivier Michael Molinari

Sylvain Turenne

Catherine Billotte Cabre

Jonathan Goering

Claude Marcel Mons

Jean-Luc Soupizon

Stephane Rousselin

Thierry Godon

François Charleux

Dominique Raulin

Michael Podgorski

Son Le Hong

Daniel G Girault

Philippe Verseux

Laurent Jean David

Caroline Aumont

Jean-Yves Guedou

Stéphane Rousselin

Jean-Francois Fromentin

Joel M Benoit

Michaël Podgorski

Edu Ruiz

Jean-François Fromentin

Jean Noel Mahieu

Jean-Noël Mahieu

Didier Escure

Alain Robert Perroux

Sebastien Bourget

Christophe Gerard Grosbois

Aymeric Hugonie

Patrick Fouche

Catherine L Guet

Ludovic Molliex

Pierre Savoyat

Sandrine Chatel

Jean-Paul Bourgeois

Sébastien Bourget

François Marlin

Régis Servant

Antoine Phelippeau

Stéphane Lévèque

Alain Perroux

Olivier Molinari

Francois Marlin

Francois Charleux

Eduardo Ruiz

Francois Trochu

Didier Rene Escure

Dominique Marie Coupe

Franck Bernard Varin

A method of fabricating a composite material part includes placing a fiber texture in a mold including in its bottom portion a porous material part on which a first face of the texture rests, injecting a liquid under pressure into the fiber texture, the liquid containing a powder of refractory ceramic particles, and draining through the porous material part the liquid that has passed through the fiber texture, while retaining the powder of refractory ceramic particles inside said texture by the porous material part. A perforated rigid element is interposed between the bottom of the mold and the porous material part.

Method of fabricating a composite material part by injecting a filled slurry into a fiber texture

A fiber blank woven as a single piece by three-dimensional weaving to make a closed box-structure platform out of composite material for a turbine engine fan. In each plane of the fiber blank, a set of warp yarns interlinks layers of weft yarns in first, second, and third portions of the fiber blank, while leaving a closed non-interlinked zone separating the first and second portions over a fraction of the dimension of the fiber blank in the warp direction between an upstream non-interlinking limit and a downstream non-interlinking limit, and while leaving at least one open non-interlinked zone separating the second and third portions over a fraction of the dimension of the fiber blank in the warp direction from a non-interlinking limit to a downstream edge of the fiber blank. A method of fabricating a preform for the closed box-structure platform can use such a fiber blank.

Fiber blank woven as a single piece by three-dimensional weaving to make a closed box-structure platform out of composite material for a turbine engine fan

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 method of fabricating a part, for example a reinforcing edge for a turbomachine blade, the method including: making at least one fiber structure by three-dimensionally weaving metal yarns; and subjecting the fiber structure to hot isostatic pressing to cause the metal yarns to agglomerate so as to obtain a solid part. A composite solid part, for example a reinforcing edge for a turbomachine blade, includes a reinforcing structure of three-dimensionally woven ceramic fibers and a metal or metal alloy matrix.

Method of fabricating a part and a composite solid part obtained by the method

A reinforcing fiber structure woven as a single piece for fabricating a composite material part, the fiber structure having an internal portion or core (), and a portion adjacent to an outside surface of the structure, or skin (), and the fiber structure being formed by a three-dimensional weaving in its core using at least one weave selected from an interlock weave and a multilayer weave, and by weaving at its skin with a weave of satin type that is different from the weave in the core the weaving at the skin being of the multilayer type or of the two-dimensional type.

Reinforcing fibrous structure for a composite material and a part containing said structure

A method of making a fiber structure by multilayer three-dimensional weaving, the fiber structure having a thickness in a direction perpendicular to the warp and weft directions that varies along the warp direction while conserving the same number of warp yarns that are woven at all points of the fiber structure along the warp direction, wherein during a transition in the warp direction from a first portion of the fiber texture to a second portion of the fiber texture having a thickness that is greater than the thickness of the first portion, the number of warp planes is decreased and the number of layers of warp yarns is increased without changing the number of warp yarns, by constituting at least one warp plane in the second portion with warp yarns taken from at least two different warp planes in the first portion.

Production of a fibrous structure with variable thickness by 3D weaving

A turbomachine comprising at least a first rotary assembly with a first shaft, a stator, and bearings secured to the stator and suitable for supporting the shaft, one of the bearings being capable of giving way when an unbalance occurs in the rotary assembly, at least one segment of the shaft being covered in a covering which comprises at least one piece of fabric impregnated with resin and which is for coming into contact with a surrounding portion of the turbomachine when the unbalance occurs in order to protect the first shaft and ensure that there is no risk of the first shaft rupturing. The turbomachine is intended to be used mainly in the field of aviation, and more particularly as an airplane turbojet.

System for protecting a main shaft of an engine having a fusible bearing

The composite turbomachine blade of the present invention comprises a preform made of yarns or fibers woven in three dimensions and a binder maintaining the relative disposition between the yarns of the preform. Said preform is made up of warp yarns and of weft yarns, the direction of the warp yarns forming the longitudinal direction of the preform. In characteristic manner, said preform comprises at least a first portion made using a first weave forming the airfoil of the blade, and a second portion made using a second weave forming the root of the blade, and the first and second portions are united by a transition zone in which the first weave is progressively modified to end up with the second weave, thereby obtaining a reduction at least in the thickness of the blade between the second portion and the first portion. The invention is applicable to making a fan blade for a turbojet.

Turbomachine blade, in particular a fan blade, and its method of manufacture

A turbomachine rotor stage having a thin annular body comprising a metal alloy part reinforced by at least one fibrous ring which has a radial height h of at least 1.5 times its axial width l and which is embedded in the metal alloy part so that it projects radially outwardly from the inner wall thereof in order to stiffen the body and reduce the quantity of fibre material to be used.

Fibre-reinforced rotor stage for a turbomachine

A gas turbine blade includes a central core covered by a plurality of layers of composite material, and optionally also an outer sleeve of woven composite material. A network of transverse seams pass through the layers of composite material, and preferably also the core and the outer sleeve. This construction is particularly applicable to large diameter turbine blades.

Gas turbine blade comprising layers of composite material

Growing community of inventors

Le Chatelet en Brie, France

Bruno Dambrine