Safran Aircraft Engines

Safran

Snecma

Michael Podgorski

Ludovic Edmond Camille Molliex

Edu Ruiz

Sylvain Turenne

Catherine Billotte Cabre

Bruno Jacques Gerard Dambrine

Philippe Charles Alain Le Biez

Bruno Jacques Gérard Dambrine

Nicolas Droz

Ludovic Philippe Liais

Serge Selezneff

Jonathan Goering

Dominique Marie Christian Coupe

Son Le Hong

Bruno Dambrine

Adrien Paixao

Michel Vilasi

Ludovic Edmond Molliex

Stéphane Mathieu

Patrice Berthod

Beryl Cassandre Anne Mereaux

Ludovic Molliex

Léo Portebois

Thierry Claude Henri Godon

Sofia Haifi

Dominique Marie Coupe

Stephane Mathieu

Leo Portebois

Ludovic Ec Molliex

Philippe Charles A Le Biez

Ludovic Liais

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

The present invention relates to an abradable coating for a turbine engine part, characterized by the fact that said coating includes a layer made of an abradable material, the surface asperities of which are filled with thermally bonded ceramic grains, forming a smooth, free surface having a low roughness.

Abradable coating made of a material having a low surface roughness

A method of fabricating a composite material part includes injecting under pressure a slurry containing a powder of refractory ceramic particles into a fiber texture; and draining the liquid of the slurry that has passed through the fiber texture, while retaining the powder of refractory ceramic particles within the texture to obtain a fiber preform filled with refractory ceramic particles. The injection tooling includes a porous material mold including an internal housing in which the fiber texture is placed, the slurry being injected into the fiber texture via an injection port in the injection tooling and leading into the internal housing of the mold. The tooling includes a rigid material enclosure in which the porous material mold is held while the slurry is injected under pressure and while the liquid of the slurry is drained, the liquid of the slurry being discharged via a vent present in the enclosure.

Process for manufacturing a ceramic composite material part by pressurized injection of a loaded slurry into a porous mould

A method of fabricating an impregnated fiber assembly, the method including introducing a first suspension including a first powder of solid particles into an inside volume defined by an inside face of a first fiber texture of hollow shape placed in a mold, an outer face of the first fiber texture being present facing a wall of the mold; using a centrifugal force to impregnate the first fiber texture with the first suspension by rotating the mold; after impregnating the first texture, positioning a second fiber texture on the inside face of the first fiber texture to obtain a fiber assembly; introducing a second suspension including a second powder of solid particles into the inside volume after putting the second fiber texture into position; and using a centrifugal force to impregnate the second fiber texture with the second suspension by rotating the mold to obtain an impregnated fiber assembly.

Method of fabricating an impregnated fiber assembly

A method of fabricating a part out of composite material, includes forming a fiber texture from refractory fibers; impregnating the fiber texture for a first time with a first slip containing first refractory particles; eliminating the liquid phase from the first slip so as to leave within the texture only the first refractory particles; impregnating the fiber texture for a second time with a second slip containing second refractory particles; eliminating the liquid phase from the second slip so as to leave within the texture only the second refractory particles and obtain a fiber preform filled with the first and second refractory particles; and sintering the first and second refractory particles present in the fiber preform in order to form a refractory matrix in the preform.

Method for manufacturing part made of composite material

A method of fabricating a part out of composite material, includes forming a fiber texture from refractory fibers; placing the texture in a mold having an impregnation chamber including in its bottom portion a part made of porous material, the impregnation chamber being closed in its top portion by a deformable impermeable diaphragm separating the impregnation chamber from a compacting chamber; injecting a slip containing a powder of refractory particles into the impregnation chamber; injecting a compression fluid into the compacting chamber, to force the slip to pass through the texture; draining the liquid of the slip via the porous material part, while retaining the powder of refractory particles inside the texture so as to obtain a fiber preform filled with refractory particles; drying the fiber preform; unmolding the preform; and sintering the refractory particles present in the preform in order to form a refractory matrix in the preform.

Method for manufacturing a refractory part made of composite material

A turbine engine part includes at least a substrate, and present on the substrate, a ceramic coating for protection against calcium and magnesium aluminosilicates, the ceramic coating including AlOat a molar content lying in the range 33% to 49%, YAlOat a molar content lying in the range 21% to 53%, and yttria-stabilized zirconia at a molar content lying in the range 13% to 31%.

Turbine engine part coated with a protective ceramic coating, method for manufacturing and for using such a part

A fiber preform for a hollow turbine engine vane, the preform including a main fiber structure obtained by three-dimensional weaving and including at least one main part, wherein the main part extends from a first link strip, includes a first main longitudinal portion forming a pressure side wall of an airfoil, an U-turn bend portion forming a leading edge or a trailing edge of the airfoil, a second main longitudinal portion facing the first main longitudinal portion and forming a suction side wall of the airfoil, and terminating at a second link strip. The first and second link strips are secured to each other and form a link portion of the main fiber structure. The main longitudinal portions are spaced apart so as to form a gap between the main longitudinal portions forming a hollow in the airfoil.

Fiber preform for a hollow turbine engine vane

A method of fabricating a fiber preform filled with refractory ceramic particles, includes placing a fiber texture including refractory ceramic fibers in a mold cavity; injecting a slip including a powder of refractory ceramic particles present in a liquid medium, the slip being injected into the pores of the fiber texture present in the mold cavity, injection being performed through at least a first face or a first edge of the fiber texture; and draining the liquid medium of the slip that has penetrated into the fiber texture through the porous material part, the draining being performed at least through a second face or a second edge of the fiber texture different from the first face or the first edge, the porous material part also serving to retain the refractory particle powder in the pores of the fiber texture to obtain a fiber preform filled with refractory particles.

Method of fabricating a fiber preform filled with refractory ceramic particles

A part made of a ceramic material, including a portion forming a base and a portion forming a wall, wherein the base consists of a low-porosity ceramic material and the wall is obtained by powder sintering and includes an envelope and a core, the core being within the envelope, the porosity of the core being higher than that of the base and increasing the further it is from the base.

Part consisting of a ceramic material, comprising a base and a wall

An oxide/oxide composite material turbomachine blade including a fiber reinforcement obtained by weaving a first plurality of threads and a second plurality of threads, with the threads of said first plurality of threads being arranged in successive layers and extending in the longitudinal direction of the fiber blank corresponding to the longitudinal direction of the blade is disclosed. The reinforcement is densified by a matrix, with the blade further including one or several internal channels having a coiled shape extending in the longitudinal direction of the blade.

Method for manufacturing an oxide/oxide composite material turbomachine blade provided with internal channels

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Paris, France

Michael Podgorski