Abstract: 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-?, 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.

Abstract: A method for manufacturing an environmental barrier comprising the steps of coating a rare earth silicate powder with a precursor of a densification agent in order to form a rare earth silicate powder coated with the precursor of the densification agent, thermally spraying the coated powder onto a substrate in order to obtain an at least partially amorphous environmental barrier on the substrate and thermally treating the environmental barrier in order to crystallize and densify the environmental barrier.

Abstract: The present invention relates to a method for the protection of a hafnium-free, nickel-based monocrystalline superalloy part against corrosion and oxidation. The method comprises at least the following steps of: manufacturing a hafnium-free, nickel-based monocrystalline superalloy part (1), depositing on the part a first hafnium-free sublayer (2), depositing, on the first sublayer (2), a second hafnium-doped sublayer (3), depositing, on the second sublayer (3), a third hafnium-free sublayer (4), sandblasting the third sublayer (4) to at least partially separate the third sublayer (4) and increase the surface roughness of an upper sub-layer formed by the second sublayer (3) and at least partially by the third sublayer (4), performing oxidation treatment so as to obtain at the surface a layer of hafnium-doped oxidised material (5), depositing a thermal barrier layer (6) on the layer of oxidised material (5).

Abstract: The invention relates to a part made of silicon-based ceramic material or silicon-based ceramic matrix composite (CMC) material comprising an environmental barrier coating (EBC), said coating (12, 13) comprising a bonding layer (12) deposited on the surface of the ceramic material or ceramic matrix composite (CMC), said bonding layer (12) being topped by one or more layers together forming a multifunctional barrier structure (13), characterised in that the bonding layer (12) has at its interface with the multifunctional structure a polycrystalline silica layer (12) or sub-layer (12b).

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.