Abstract: 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.

Abstract: The present invention relates to a turbine part, comprising a substrate, an environmental barrier comprising at least one layer selected from a thermally insulating layer, a sub-layer adapted to promote adhesion between the substrate and a thermally insulating layer, and a protective layer adapted to protect the substrate from oxidation and/or corrosion, the environmental barrier at least partially covering the substrate, at least one reactive layer being adapted to react with at least one CMAS compound, the reactive layer covering at least part of the environmental barrier. The invention is characterized in that the material of the reactive layer comprises an oxide of formula A?A?BO5-?, A? being selected from a rare earth and yttrium, A? being selected from a rare earth yttrium and aluminum, B being selected from titanium, zirconium, lufnium, tantlum and niobium, wherein ? is a real number between 0 and 0.5.

Abstract: A coated gas turbine engine part includes a substrate and a calcium-magnesium-alumino-silicate (CMAS) protection layer present on the substrate. The protection layer includes a first phase of a calcium-magnesium-alumino-silicate CMAS protection material capable of forming an apatite or anorthite phase in the presence of calcium-magnesium-alumino-silicates CMAS and a second phase including particles of at least one rare-earth REa silicate dispersed in the first phase.

Abstract: 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.

Abstract: 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.