Safran Aircraft Engines

Safran

Other

Snecma

Ludovic Edmond Camille Molliex

Michael Podgorski

Bruno Jacques Gerard Dambrine

Philippe Charles Alain Le Biez

Bruno Jacques Gérard Dambrine

Sylvain Turenne

Edu Ruiz

Serge Selezneff

Catherine Billotte Cabre

Jonathan Goering

Stephane Rousselin

Dominique Marie Christian Coupe

Didier Rene Andre Escure

Son Le Hong

Marcel Garnier

Julien Schneider

Daniel G Girault

Caroline Aumont

Jean-Francois Fromentin

Beryl Cassandre Anne Mereaux

Jean-Yves Guedou

Sandrine Chatel

G&eacute;rard Philippe Gauthier

Jean Hamburger

Yves Christian Louis Alain Honnorat

Jose Feigenblum

Gerard Weiss

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 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 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 identifying and/or tracking deformation of a mechanical part made of composite material for a turbine engine, in which the part includes a preform of fiber material and a resin, is provided. The method includes incorporating metal particles in the preform or the resin during fabrication of the part, and subjecting the mechanical part to two X-ray inspections on two different occasions so as to identify the part and/or so as to deduce deformation of its internal structure.

Method of identifying and/or tracking deformation of a turbine engine part

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

A turbomachine rotor including at least one disk having a ring constituted, for example, by a winding of metal-coated silicon carbide or alumina yarn. According to the invention, the composite ring is received in a closed annular cavity, e.g. defining by machining a groove in an enlarged portion of the disk and closing the groove by means of an annular plate after the ring has been put into place.

Turbomachine rotor including at least one disk reinforced by a composite ring

The invention concerns a method for producing parts made of thin, light and rigid metal alloy essentially having the following steps: producing a core having the part shape; producing cavities in the core; producing shells made of metal alloy combined with reinforcing fibers with high modulus of elasticity; densifying the shells; and diffusion welding of the shells on the core by compression at temperature and pressure conditions for isothermal forging of the metal alloy used.

Method for obtaining thin, light and rigid metal parts

The invention concerns a method for metal coating of fibres (,) by liquid process, said method being particularly but not exclusively designed for coating in thick and even layers (,) with metals and metal alloys having high melting point and reactivity. Said method is characterised in that it consists in moving along the stretched fibre (,) in the liquid metal maintained in levitation in a well (,), said fibre (,) passing through orifices (,) provided in the well (,) wall (,), said orifices (,) being arranged on either side of the liquid metal at places where the liquid metal (,) is not in contact with said wall (,).

Method for metal coating of fibres by liquid process

Growing community of inventors

Brunoy, France

Ludovic Edmond Camille Molliex