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: A component includes a substrate at least a portion of which adjacent to a surface of the substrate is made of a material including silicon; a bond coat located on the surface of the substrate and including silicon, an environmental barrier which includes an outer layer of ceramic material covering the bond coat, wherein the environmental barrier further includes a self-healing inner layer located between the bond coat and the outer layer, the inner layer including a matrix in which silico-forming particles are dispersed, these particles being capable of generating a matrix crack healing phase in the presence of oxygen.

Abstract: A part made from a composite material having a ceramic matrix and including a protection device, the protection including a coating layer having a gradual composition. The gradual-composition coating layer includes at least one silicon phase and one aluminium phase, the proportions of which change according to the height in the layer, with a first height in the gradual-composition coating layer corresponding to a silicon-free composition, and a second height corresponding to an aluminium-free composition. A method for producing such a protection, and to a device for carrying out the method, are disclosed.

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 component includes a substrate at least a portion of which adjacent to a surface of the substrate is made of a material including silicon; a bond coat located on the surface of the substrate and including silicon, an environmental barrier which includes an outer layer of ceramic material covering the bond coat, wherein the environmental barrier further includes a self-healing inner layer located between the bond coat and the outer layer, the inner layer including a matrix in which silico-forming particles are dispersed, these particles being capable of generating a matrix crack healing phase in the presence of oxygen.

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: A method for coating at least one surface of a solid substrate with at least one layer comprising at least one ceramic compound by a suspension plasma spraying (SPS) technique, in which at least one suspension of solid particles of at least one ceramic compound is injected into a plasma jet, and then the thermal jet that contains the solid particle suspension is sprayed onto the surface of the substrate, by way of which the layer comprising at least one ceramic compound is formed on the surface of the substrate; method characterised in that, in the suspension, at least 90 vol % of the solid particles have a larger dimension (referred to as d90), such as a diameter, smaller than 15 ?m, preferably smaller than 10 ?m, and at least 50 vol % of the solid particles have a larger dimension, such as a diameter (referred to as d50), no smaller than 1 ?m. A substrate coated with at least one layer that can be obtained by the method.

Abstract: A method for preparing a protective coating against oxidation on at least one surface of at least one part made of at least one material capable of being oxidized, wherein the following successive steps are carried out: a) each of the particles of a powder made of a first ceramic selected from refractory ceramics and ceramics which resist oxidation, is coated with at least one layer selected from layers made of a refractory ceramic, layers made of a ceramic which resist oxidation, and layers made of a refractory metal, provided that the coating comprises at least one ceramic which resists oxidation, and at least one refractory ceramic or metal; b) the powder is deposited onto the surface to be coated of the part; c) sintering of the powder is achieved on the surface of the part by a Spark Plasma Sintering (SPS) Method; d) the part is cooled; e) the cooled part, coated on at least one of its surfaces with a protective refractory monolayer coating against oxidation, with a three-dimensional microstructure, i

Abstract: The invention relates to the field of the coating of substrates with an abradable material. More specifically it relates to a method for coating at least one surface of a substrate with at least one ceramic compound, as well as to a thereby obtained coating. It also relates to a substrate having at least one surface coated with such a coating. It further relates to a device for applying the coating method. Applications: fields of mechanical engineering and aeronautical design.

Abstract: A method for preparing a protective coating against oxidation on at least one surface of at least one part made of at least one material capable of being oxidized, wherein the following successive steps are carried out: a) each of the particles of a powder made of a first ceramic selected from refractory ceramics and ceramics which resist oxidation, is coated with at least one layer selected from layers made of a refractory ceramic, layers made of a ceramic which resist oxidation, and layers made of a refractory metal, provided that the coating comprises at least one ceramic which resists oxidation, and at least one refractory ceramic or metal; b) the powder is deposited onto the surface to be coated of the part; c) sintering of the powder is achieved on the surface of the part by a Spark Plasma Sintering (SPS) Method; d) the part is cooled; e) the cooled part, coated on at least one of its surfaces with a protective refractory monolayer coating against oxidation, with a three-dimensional microstructure, i

Abstract: The invention relates to a composite material element (1), the composite material comprising a microfissured matrix (7) in the form of a three-dimensional interconnected network (4) of microfissures exposed on the surface of the ceramic matrix, an additive material (6) consisting of a flux or glass being dispersed in the matrix, the additive material (6) being a material which, when the composite material is brought to a predetermined temperature, softens and migrates by capillarity in the network (4) of microfissures (4) to said surface of the element. The quantity of additive material dispersed initially in the matrix is in a sufficient proportion compared to the matrix intended to coat a surface (5) of the composite material element left exposed so as to create a gas-tight barrier.

Abstract: Process for producing at least one nanoporous layer of nanoparticles chosen from nanoparticles of a metal oxide, nanoparticles of metal oxides, and mixtures of said nanoparticles, on a surface of a substrate, in which at least one colloidal sol, in which said nanoparticles are dispersed and stabilized, is injected into a thermal plasma jet which sprays said nanoparticles onto said surface. Nanoporous layer and device, especially a separation device, comprizing said layer.

Abstract: The invention relates to a fuel cell consisting of a stack of elementary cells and interconnectors (7) and comprising a single vertical seal (2) which is placed around the stack thus formed. The aforementioned assembly is preferably equipped with a containment tube (1) which is placed around the vertical seal (2). Supply channels (11 and 12) in the interconnectors and lateral inlet and outlet (13 and 14) holes can be used to supply distribution channels (9 and 10) which are positioned against the electrodes of each elementary cell. The invention is suitable for SOFC-type fuel cells.

Abstract: Process for producing at least one nanoporous layer of nanoparticles chosen from nanoparticles of a metal oxide, nanoparticles of metal oxides, and mixtures of said nanoparticles, on a surface of a substrate, in which at least one colloidal sol, in which said nanoparticles are dispersed and stabilized, is injected into a thermal plasma jet which sprays said nanoparticles onto said surface. Nanoporous layer and device, especially a separation device, comprizing said layer.

Abstract: The invention relates to a composite material element (1), the composite material comprising a microfissured matrix (7) in the form of a three-dimensional interconnected network (4) of microfissures exposed on the surface of the ceramic matrix, an additive material (6) consisting of a flux or glass being dispersed in the matrix, the additive material (6) being a material which, when the composite material is brought to a predetermined temperature, softens and migrates by capillarity in the network (4) of microfissures (4) to said surface of the element. The quantity of additive material dispersed initially in the matrix is in a sufficient proportion compared to the matrix intended to coat a surface (5) of the composite material element left exposed so as to create a gas-tight barrier.

Abstract: The invention relates to a fuel cell consisting of a stack of elementary cells and interconnectors (7) and comprising a single vertical seal (2) which is placed around the stack thus formed. The aforementioned assembly is preferably equipped with a containment tube (1) which is placed around the vertical seal (2). Supply channels (11 and 12) in the interconnectors and lateral inlet and outlet (13 and 14) holes can be used to supply distribution channels (9 and 10) which are positioned against the electrodes of each elementary cell. The invention is suitable for SOFC-type fuel cells.

Abstract: The present invention relates to a method of coating a surface with nanoparticles, to a nanostructured coating that can be obtained by this method, and also to a device for implementing the method of the invention. The method is characterized in that it comprises an injection of a colloidal sol of said nanoparticles into a plasma jet that sprays them onto said surface. The device (1) comprises: a plasma torch (3); at least one container (5) containing the colloidal sol (7) of nanoparticles; a device (9) for fixing and for moving the substrate(S); and a device (11) for injecting the colloidal sol into the plasma jet (13) of the plasma torch. The present invention has applications in optical, electronic and energy devices (cells, thermal barriers) comprising a nanostructured coating that can be obtained by the method of the invention.