Safran

Commissariat a L'energie Atomique

Centre National De La Recherche Scientifique

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

Luc Bianchi

Aurélien Joulia

Benjamin Dominique Roger Joseph Bernard

Amar Saboundji

David Guenadou

Philippe Belleville

Pierre Jean Sallot

Alexandre Allemand

Yann Le Petitcorps

Hugues Denis Joubert

Bruno Pintault

André Hubert Louis Malie

Karine Valle

Joël Toulc'Hoat

Olivier Szwedek

Laure Cornilleau

Séchel Methout

Philippe Picot

Christophe Boscher

Charles Bories

Benjamin Bernard

Emmanuel Herve

Karine Wittmann-Teneze

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 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.

Part comprising a protective coating having a gradual composition

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 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 (), depositing on the part a first hafnium-free sublayer (), depositing, on the first sublayer (), a second hafnium-doped sublayer (), depositing, on the second sublayer (), a third hafnium-free sublayer (), sandblasting the third sublayer () to at least partially separate the third sublayer () and increase the surface roughness of an upper sub-layer formed by the second sublayer () and at least partially by the third sublayer (), performing oxidation treatment so as to obtain at the surface a layer of hafnium-doped oxidised material (), depositing a thermal barrier layer () on the layer of oxidised material ().

Method for protection against corrosion

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 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.

Component protected by an environmental barrier

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:

Process for coating a part with an oxidation-protective coating

The invention relates to a composite material element (), the composite material comprising a microfissured matrix () in the form of a three-dimensional interconnected network () of microfissures exposed on the surface of the ceramic matrix, an additive material () consisting of a flux or glass being dispersed in the matrix, the additive material () being a material which, when the composite material is brought to a predetermined temperature, softens and migrates by capillarity in the network () of microfissures () 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 () of the composite material element left exposed so as to create a gas-tight barrier.

Solid joint obtained by heat projection

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.

Process for producing a nanoporous layer of nanoparticles and layer thus obtained

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

Growing community of inventors

Moissy-Cramayel, France

Luc Bianchi