Societe Europeenne De Propulsion

Snecma Propulsion Solide

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

Centre National De La Recherche Scientifique

Herakles

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

Snecma Moteurs

Societe European De Propulsion

Arianegroup Sas

Jacques Thebault

Michel Laxague

Christian Robin-Brosse

Jean-Luc Domblides

Laurent David

Pierre Olry

Bruno C Bernard

René Pailler

Lionel Vandenbulcke

Jacques Rey

Jean-Christophe Ichard

Rodolphe Delaval

Gerard Palavit

Marc Lacoste

Anne Sauveroche

Dominique Coupe

Jean-Pierre Maumus

Sébastien Bertrand

Rene Pailler

Bernard Delperier

Roger Naslain

Stéphane Goujard

Eric Lavasserie

Francis Rebillat

Louis G Heraud

Pascal Diss

Hervé Evrard

Jean-Luc Leluan

Bernard Buttazzoni

Francois Beguin

Jean-Philippe Rocher

Jean-Pierre Ciais

Yves D Patrigeon

Aline Balhadere

Alain Nale

St&eacute;phane Goujard

Gilles Bondieu

Angeline Poulon

Clément Bouquet

Jacques Cotteret

Georges Constant, Deceased

Philippe Leseur

Anne-Sophie Andreani

Jean-Marie Toussaint

Emilie Courcot Mendez

Alain Seron

Aurélie Quet

Jean-Eric Pelletan

Philippe Girard

Jean L Domblides

Jean Michel Georges

Yves Madec

Emilie Courcot

Ageline Poulon

Bruno Bernard

A refractory material that can withstand high temperatures in an oxidizing medium and containing at least: The material contains neither silicon nor a compound of silicon.

Materials and parts that can withstand high temperatures in an oxidizing medium, and method for manufacturing same

A refractory material withstanding high temperatures in an oxidizing medium contains at least hafnium boride and tantalum boride, hafnium and tantalum being present in the refractory material exclusively in compound form.

Ultra-refractory material that is stable in a wet environment, and process for manufacturing same

The invention relates to a method of making a refractory carbide layer on the accessible surface of a C/C composite material, the method including a step consisting in placing the composite material in contact with a reactive composition in solid form that contains an atomic proportion greater than or equal to one-third and less than or equal to 95% of a metal that is a precursor of a determined carbide having a melting temperature greater than 2000&#xb0; C., and an atomic proportion of silicon that is greater than or equal to 5% and less than or equal to two-thirds. The method further includes a step consisting in impregnating the accessible surface of the C/C composite material with the reactive composition melted at a temperature that is greater than or equal to the melting temperature of the metal that is a precursor of a determined carbide.

Method for making a refractory carbide layer on a part made of C/C composite material

Within the pores of a porous thermostructural composite material, there is form an aerogel or xerogel made up of a precursor for a refractory material, the precursor is transformed by pyrolysis to obtain an aerogel or xerogel of refractory material, and then it is silicided by being impregnated with a molten silicon type phase. The aerogel or xerogel is formed by impregnating the composite material with a composition containing at least one organic, organometalloid, or organometallic compound in solution, followed by in situ gelling. The method is applicable to improving the tribological properties or the thermal conductivity of C/C or C/SiC composite material parts, or to making such parts leakproof.

Method of siliciding thermostructural composite materials, and parts obtained by the method

A method of densifying a porous substrate with pyrolytic carbon includes loading the substrate into an oven, admitting a reaction gas mixture to the oven, extracting an effluent gas from the oven, and recycling components of the effluent gas into the reaction gas mixture. The reaction gas mixture contains a pyrolytic carbon precursor gas together with a vector gas. The effluent gas contains residual components of the reaction gas mixture together with reaction products, including hydrogen. The recycling is performed after eliminating heavy hydrocarbons contained in the effluent gas.

Method for chemical infiltration in the gas phase for the densification of porous substrates with pyrolytic carbon

A method of manufacturing a part out of impervious thermostructural composite material, the method comprising forming a porous substrate from at least one fiber reinforcement made of refractory fibers, and densifying the reinforcement by a first phase of carbon and by a second phase of silicon carbide. The method then continues by impregnating the porous substrate with a composition based on molten silicon so as to fill in the pores of the substrate.

Method of manufacturing a part out of impervious thermostructural composite material

Thermostructural composite structure having a compositional gradient, formed from a porous core () made of a refractory having a pore volume content of greater than or equal to 80%. The core () lies between two intermediate layers () comprising the carbon fiber reinforcement, densified by a matrix composed of the carbon phase and of a ceramic phase, and a refractory solid filler. Two monolithic ceramic shells () cover the intermediate layers in order to give stiffness to the entire structure.

Thermostructural composite structure with a compositional gradient, its manufacturing process

Thermostructural composite structure with a compositional gradient and its manufacturing process

A method and apparatus for a continuous coating of a part may include providing a separation layer made of a material that is weaker than the material of the coating to be made. The part may be placed on one or more supports, the supports coated with the separation layer. A continuity layer of a component material of the coating to be made is interposed between the part and the or each support, at least in vicinity of the or each support zone. The coating is formed by chemical vapor infiltration or deposition, and the part is then separated from the or each support by rupture within the separation layer, the continuity of the coating of the part in the or each support zone being provided by the portion of the coating that comes from the continuity layer that remains in place on the part.

Method of making a continuous coating on the surface of a part

An oxidation-sensitive composite has applied thereto a composition comprising a mixture of boride powder constituted for the most part of TiB , at least one vitreous refractory oxide powder constituted for the most part by a mixture of borosilicate glass, and a binder containing a ceramic-precursor resin. The resin is cured and is subsequently transformed into a ceramic by heat treatment or during first exposure of the coated part to high temperatures.

Protecting composite material parts against oxidation

Prior to housing the crucible in the bowl, a consumable buffer ply is applied over at least a portion of the inside face of the bowl, the ply being constituted essentially by a non-rigid carbon fiber fabric for protecting the bowl from both physical and chemical interactions with the crucible. The buffer ply is essentially constituted by a flexible fabric selected from: a woven cloth, a knit, a multidirectional sheet, and a thin felt. Prior to putting the ply into place in the bowl, it is possible to form a thin deposit of pyrolytic carbon on the fibers of the fabric.

Protection for a carbon material, in particular C/C composite, bowl that is to receive a crucible, such as a silica crucible for drawing silicon

The invention concerns (1) thermochemically treating by pack-cementation a carbon-containing material, which may have an open porosity, to generate a refractory carbide coating on its surface and, if the material is porous, within the material; and (2) the use of specific alloys as a pack for thermochemically treating carbon-containing materials, optionally with an open porosity, in a halogenated atmosphere. Pack-cementation is carried out under reduced pressure using an element E (to be transported and to be reacted with the carbon in the material to generate the expected carbide) alloyed to an element M, and using a halide (chloride or fluoride, preferably a fluoride) of the same element M, of low volatility, present in the solid form.

Thermochemical treatment, in halogenated atmosphere, of a carbon-containing material

The present invention provides a method of densifying porous structures by chemical vapor infiltration. In characteristic manner, said densification method is implemented using toluene as a precursor for carbon. Said toluene is generally used mixed with at least one carrier gas.

CVI (chemical vapor infiltration) densification of porous structures

Method for making an internal combustion engine piston in

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Bordeaux, France

Jacques Thebault