Safran Ceramics

Centre National De La Recherche Scientifique

Safran Aircraft Engines

Universitë De Bordeaux

Safran

Lisa Pin

Simon Arnal

Philippe Charles Alain Le Biez

Serge Georges Vladimir Selezneff

Francis Rebillat

Nicolas Droz

Fabrice Mauvy

Eric Bouillon

Eric Conete

David Marsal

Maxime François Roger Carlin

Aurélia Clerambourg

Maxime Carlin

Ioannis Stasinopoulos

Jean-François Henne

Adèle Lyprendi

A part includes a substrate made of ceramic matrix composite material, the substrate being coated with a multilayer stack including at least, and in this order, starting from the substrate a tie layer including silicon; an insulation layer including a rare earth disilicate or silica; a barrier layer including a rare earth disilicate; the part further including at least one thermocouple inserted between the insulation layer and the barrier layer.

CMC materials with integrated thermocouple

An abradable coating for a turbomachine part, includes a matrix made of a first metal material and particles made of a second metal material that are dispersed in the matrix, the first metal material having a melting temperature greater than 900° C., the second metal material having a melting temperature at least 50° C. lower than the melting temperature of the first metal material.

Abradable coating for rotating blades of a turbomachine

A method for coating a ceramic matrix composite part with an environmental barrier, the method including a) applying, to a surface of the part, a coating composition including a first powder of a rare earth silicate and a second powder including boron, the coating composition having a ratio R=[mass of the second powder]/[mass of the first powder] of between 0.1% and 5%, and b) sintering the first and second powders to obtain the environmental barrier on the part.

Method for coating a ceramic matrix composite part with an environmental barrier

A part includes a substrate, having, adjacent to a surface of the substrate, at least a portion that is made from a material that contains silicon, and an environmental barrier formed on the surface of the substrate, the environmental barrier including at least a first layer including a rare earth disilicate of formula RESiOpresent at a molar content lying in the range 70% to 99.9%, where REis a rare earth element; and at least one rare earth oxide of formula REOpresent at a molar content lying in the range 0.1% to 30%, where REis a rare earth element different from RE.

Part comprising a substrate and an environmental barrier

A part includes a substrate having, adjacent to a surface of the substrate, at least a portion that is made of a material that contains silicon, and an environmental barrier formed on the surface of the substrate, the environmental barrier including a first layer including at least one first rare earth silicate and presenting grains with a mean size less than or equal to 1 &#x3bc;m; and a second layer covering the first layer, the second layer including at least one rare earth silicate and presenting grains with a mean size greater than 1 &#x3bc;m.

An abradable coating includes a matrix and particles that are dispersed in the matrix, the particles being made of a material switching into a fluid phase under the effect of the increase in temperature upon contact between a tip of a blading and the abradable coating.

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

A turbine ring sector made of ceramic matrix composite material has a portion forming an annular base with an inner face for defining the inner face of a turbine ring when the ring sector is mounted on a ring support structure and an outer face from which there extends an attachment portion for attaching the ring sector to the ring support structure, the ring sector further including inter-sector faces, each for facing a neighboring ring sector when the ring sector is mounted on the ring support structure; wherein the inter-sector faces are coated in an environmental barrier that is doped with an electrically-conductive compound and that presents at least one slot.

Growing community of inventors

Moissy-Cramayel, France

Lisa Pin