Safran Ceramics

Snecma Propulsion Solide

Herakles

Centre National De La Recherche Scientifique

Universitë De Bordeaux

Snecma

Societe Europeenne De Propulsion

Arianegroup Sas

Sapran Ceramics

Safran Aircraft Engines

Messier-bugatti Inc.

Eric Bouillon

Eric Philippe

Dominique Coupe

Arnaud Delehouze

Nicolas Eberling-Fux

Rémi Bouvier

Caroline Louchet-Pouillerie

Georges Habarou

Adrien Delcamp

Henri Tawil

Eric Lavasserie

François Charleux

Sébastien Bertrand

Julien Mateo

Bruno Dambrine

Cédric Descamps

Aurélia Clerambourg

Laurence Maille

Simon Arnal

Maxime François Roger Carlin

Matthieu Arnaud Gimat

Eric Conete

Stephane Pierre Guillaume Blanchard

Clement Roussille

Stéphane Pierre Guillaume Blanchard

Serge Chateigner

Remi Bouvier

Gildas Garnier

Nathalie Dominique Bertrand

Alain Jean-Michel Guette

Clément Roussille

Franck Lamouroux

Michael James Verrilli

Benoit Carrere

René Pailler

Stéphane Goujard

Pierre Camy

Lisa Pin

Francis Rebillat

David Marsal

Clément Marie Benoît Roussille

Sylvain Jacques

Pascal Diss

Guy M Jacob

Jean-Luc Leluan

Thomas Vandellos

Jean-Michel Guirman

Alain Caillaud

Stéphane Otin

Arnaud Fillion

Yann Lepetitcorps

Hubert Illand

Jean Noel Mahieu

Sébastien Jimenez

Emilie Courcot

Jean-Christophe Ichard

Eddy Goullianne

Amandine Lorriaux

Amine El Mansouri

Andre Lafond

Lallie Claudie Régine Quemeras

Thibault Mouret

Armine El Mansouri

Gérard Gueldry

Nicolas Eberling-fux

Robert Bagat

Brice Taillet

Francois Charleux

Nicolas Otin

Sylvain Lucien Jacques

Francis Teyssandier

André Lafond

A part made of coated composite material, includes a substrate made of ceramic matrix composite material; a tie-coat layer covering the substrate; and a protective coating on the tie-coat layer and defining an environmental barrier, the protective coating including a rare-earth silicate and including a first outer region including an outer surface of the protective coating opposite to the substrate and having a first working creep, having deformation of less than or equal to 0.07% when a compressive stress of at least 50 MPa is applied for a duration of 10 hours at a temperature of between 1050° C. and 1300° C. The first region includes a grain growth inhibitor; and a second, inner, environmental barrier region, including an interface of the protective coating with the tie-coat layer and having a second working creep.

Part made of composite material, having controlled creep

A part includes a substrate of ceramic matrix composite material, the substrate including silicon, the part further including an environmental barrier formed on at least one surface of the substrate, wherein the environmental barrier includes at least one compound selected from YbGdSiOand YbGdSiO, where γ is between 0.05 and 0.15, and wherein the environmental barrier further includes alumina AlO, the molar alumina content being between 5% and 15% of the total environmental barrier composition.

Environmental barrier for a substrate comprising free silicon

A method for coating fibres includes coating short fibres having an average length less than or equal to 5 mm by chemical vapour deposition in a fluidised bed, the short fibres treated being made of ceramic material or carbon and being mixed with spacer particles distinct from the short fibres, the spacer particles having an average diameter greater than or equal to 20 μm.

Method for coating short fibres

A method for manufacturing a composite panel is described. The method includes producing a first wall, a second wall, a third wall and a fourth wall from composite materials including an oxide matrix and long oxide fibres; from the first and second walls, producing a cellular core including a plurality of cells, each cell including a first end and an opposing second end, covering the first and second ends of the cells of the cellular core with the third wall and the fourth wall, respectively, so as to close the ends of said cells.

Method for manufacturing an acoustic panel

A process for manufacturing a part made of composite material with a matrix at least predominantly made of ceramic includes producing a fibrous structure by three-dimensional or multilayer weaving; shaping the fibrous structure to form a fibrous preform core; depositing an interphase on the fibers of the preform core; consolidating the preform core by partial densification of the core including the formation of a matrix phase by chemical vapor infiltration or by a liquid process; depositing a powder of ceramic particles in the porosity of the preform core; draping one or more layers of pre-impregnated non-woven fibers over all or part of the outer surface of the preform core; heat treatment of the preform core and of the pre-impregnated layer(s) to form a hybrid fibrous preform; further densifying by infiltration of the hybrid fibrous preform with an infiltration composition containing at least silicon to obtain a ceramic matrix composite part.

Method for manufacturing a part made from CMC

A method for producing a part having improved resistance to oxidation and high temperature-corrosion, includes the formation of an environmental barrier coating on an at least partially ceramic matrix composite material, the environmental barrier coating being formed by direct liquid injection-metal organic chemical vapor deposition.

Method for manufacturing an environmental barrier

An annular or semi-annular acoustic attenuation structure includes an inner skin and an outer skin, defining between them an annular or semi-annular volume, and a plurality of partitions extending in the space in a radial direction perpendicular to the inner and outer skins and in a circumferential direction. The inner and outer skins and the partitions are made of composite material including a fibrous reinforcement densified by a matrix. The fibrous reinforcement of each partition includes yarns or fibers extending into the fibrous reinforcement of at least one of the inner or outer skins.

Acoustic attenuation structure made of composite material and method for manufacturing same

A method for manufacturing a turbomachine blade made of ceramic matrix composite component includes at least a structural part and a functional part secured to the structural part, the method including obtaining an assembly including a first preform of the functional part that is mounted on a second preform of the structural part or on the structural part, the first preform including a fibrous reinforcement of short fibres, and the second preform or the structural part comprising a woven fibrous reinforcement, and densification of the first preform of the assembly by infiltration with a molten composition.

Method for manufacturing a ceramic matrix composite part

A process for depositing a coating on a continuous fibre of carbon or silicon carbide from a precursor of the coating, includes heating a segment of the fibre in the presence of the coating precursor in a microwave field so as to bring the surface of the segment to a temperature allowing the coating to form on the segment from the coating precursor, wherein the segment of fibre is in the presence of a supercritical phase of the precursor of the coating in the reactor and the coating is formed by supercritical phase chemical deposition in the reactor.

Method and device for depositing a coating on a continuous fibre

A method for coating fibers, includes desizing sized short fibers having an average length less than or equal to 5 mm, the short fibers being made of ceramic material or carbon, sieving the desized short fibers in order to separate them from any agglomerates of sized short fibers still present, introducing the desized and sieved short fibers into a reactor, and coating the short fibers in the reactor by chemical vapor deposition in a fluidized bed.

Method for coating fibers in a fluidized bed

A turbine stator blade made of ceramic matrix composite material includes a hollow blade profile and has a trailing edge and a leading edge, the blade including a first portion including an extrados face and a second portion distinct from the first portion including an intrados face, the first and second portions being connected to one another by a connection interface present at least on the trailing edge or leading edge, the connecting interface including a region of overlap between the first and second portions present on at least one longitudinal end of the blade profile and intended to be present outside a flow path of a gas stream of the turbine, the blade also including a platform present at a longitudinal end of the blade profile and that includes a first portion integral with the extrados face and a second part integral with the intrados face.

Turbine stator blade made of ceramic matrix composite material

A process for manufacturing a friction component made of composite material, includes the densification of a fibrous preform of carbon yarns by a matrix including at least pyrocarbon and at least one ZrOCphase, where 1&#x2264;x&#x2264;2 and 0&#x2264;y&#x2264;1, the matrix being formed by chemical vapor infiltration at least from a first gaseous precursor of pyrocarbon and a second gaseous precursor including zirconium, the second precursor being an alcohol or a Cto Cpolyalcohol modified by linking the oxygen atom of at least one alcohol function to a group of formula &#x2014;Zr&#x2014;R, the substituents R being identical or different, and R being selected from: &#x2014;H, Cto Ccarbon chains and halogen atoms.

Process for manufacturing a composite friction component

A process for depositing a coating on a continuous carbon or silicon carbide fibre from a coating precursor, includes at least heating a segment of the fibre in the presence of the coating precursor in a microwave field so as to bring the surface of the segment to a temperature enabling the coating to be formed on the segment from the coating precursor.

A process for manufacturing a composite material part including a particulate reinforcement densified by a ceramic matrix, the process including: formation of a blank of the part to be manufactured by shaping a mixture including a binder, first ceramic or carbon particles intended to form the particulate reinforcement of the part and second ceramic or carbon particles distinct from the first particles, removal or pyrolysis of the binder present in the blank to obtain a porous preform of the part to be manufactured, and infiltration of the porosity of the preform by a molten composition including a metal in order to obtain the part.

Method for producing a composite part containing a ceramic matrix

A part made of composite material includes fiber reinforcement including silicon carbide fibers presenting an oxygen content less than or equal to 1 % in atomic percentage; and a matrix present in the pores of the fiber reinforcement and including at least one sintered silicate phase including at least one rare earth silicate, mullite, or a mixture of mullite and of at least one rare earth silicate, the matrix including at least a first phase including mullite and a second phase, different from the first phase, including at least one rare earth silicate.

Composite material part

Growing community of inventors

Le Haillan, France

Eric Bouillon