Safran

Benjamin Dominique Roger Joseph Bernard

Luc Bianchi

Aurélien Joulia

André Hubert Louis Malie

A turbine part includes a substrate, an environmental barrier and one or more reactive layers. The environmental barrier includes a thermal insulation layer, a sublayer suitable for promoting adhesion between the substrate and the thermal insulation layer, and a protective layer suitable for protecting the substrate from oxidation and/or corrosion and partially covers the substrate. The one or more reactive layers are suitable for reacting with at least one CMAS compound selected from a calcium oxide, a magnesium oxide, an aluminum oxide and a silicon oxide, and cover a portion of the environmental barrier.

Fused sand-resistant turbine part

The invention relates to a turbomachine part comprising a substrate consisting of a metal material, or a composite material, and also comprising a layer of a coating for protection against the infiltration of CMAS-type compounds, at least partially covering the surface of the substrate, the protective coating layer comprising a plurality of elementary layers including elementary layers of a first assembly of elementary layers inserted between elementary layers of a second assembly of elementary layers, each elementary layer of the first assembly and each elementary layer of the second assembly comprising an anti-CMAS compound, and each contact zone between an elementary layer of the first assembly and an elementary layer of the second assembly forming an interface conducive to the spreading of cracks along said interface.

Part coated with a composition for protection against CMAS with controlled cracking, and corresponding treatment method

The invention relates to an aeronautical part, such as, for example, a turbine blade or a distributor vane, which is used in aeronautics, comprising at least one reactive layer adapted to react with at least one CMAS compound, the reactive layer at least partially covering the environmental barrier, characterized in that the material of the reactive layer comprises at least one oxide of the formula A′4-xA″xB′2-yB″yO11-δ, A′ being selected from a rare earth, yttrium and scandium, A″ being selected from a rare earth, yttrium, scandium and aluminum, B′ being selected from tantalum and niobium, B″ being selected from tantalum, niobium, titanium, zirconium, hafnium, aluminum and cesium, wherein x and y are real numbers between 0 and 2 and 6 is a real number between −1 and 2 and preferably between −1 and 1.

Fused sand-resistant aeronautical part

A coated gas turbine engine part includes a substrate and a calcium-magnesium-alumino-silicate CMAS protection layer present on the substrate. The layer includes a first phase of a calcium-magnesium-alumino-silicate CMAS protection material and a second phase including particles of an anti-wetting material dispersed in the first phase.

Growing community of inventors

Moissy-Cramayel, France

Benjamin Dominique Roger Joseph Bernard