Safran

Centre National De La Recherche Scientifique

Safran Aircraft Engines

Université Paul Sabatier (toulouse Iii)

Commissariat &#xc0; L'&#xc9;nergie Atomique Et Aux &#xc9;nergies Alternatives

Aurélien Joulia

Luc Bianchi

Benjamin Dominique Roger Joseph Bernard

André Hubert Louis Malie

Pierre Jean Sallot

Sandrine Duluard

Florence Ansart

Jawad Badreddine

Nihad Ben Salah

Elodie Marie Delon

Benjamin Bernard

Aurélie Quet

Emmanuel Herve

André 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

A coated part includes a metallic substrate, a thermal barrier comprising a ceramic material and covering the metallic substrate, wherein the coated part further includes a protective coating covering the thermal barrier, the protective coating including, in a first region, a first MAX phase, denoted PZ2, of formula (ZrTi)AlC or a first MAX phase, denoted PC2, of formula (CrTi)AlC with x non-zero and less than or equal to 1 in the MAX phases PZ2 and PC2, and the protective coating includes, in a second region covering the first region, a second MAX phase of formula TiAlC.

Coated part comprising a protective coating based on MAX phases

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.

Anti-CMAS coating with enhanced efficiency

A turbine engine part coated in at least a first ceramic layer forming a thermal barrier and including a ceramic material with first ceramic fibers dispersed in the first layer. The first layer may have a chemical composition gradient between a material for forming a thermal barrier and a material for providing protection against calcium and magnesium aluminosilicates, which is present at a greater content in an outer zone of the first layer, and/or the first layer may be porous and may present a porosity gradient such that an outer portion of the first layer presents lower porosity.

Turbine engine part coated in a thermal barrier, and a method of obtaining it

Growing community of inventors

Moissy-Cramayel, France

Aurélien Joulia