Safran Aircraft Engines

Centre National De La Recherche Scientifique

Safran

Université Paul Sabatier (Toulouse III)

Institut National Polytechnique

André Hubert Louis Malie

Justine Menuey

Florence Ansart

Aurélien Joulia

Luc Bianchi

Jean-Pierre Bonino

Sandrine Duluard

Sarah Hamadi

Pascal Fabrice Bilhe

Benjamin Dominique Roger Joseph Bernard

Hélène Cerda

Elodie Marie Delon

Guillaume Pujol

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

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

A part coated in a protective coating forms a thermal barrier and includes a ceramic first layer. The protective coating further includes a second layer present on the first layer and including a majority by weight of a first feldspar mineral having a melting temperature higher than or equal to 1010&#xb0; C. and presenting a thickness greater than or equal to 10 &#x3bc;m.

Part coated with a coating for protection against CMAS

A method of localized repair to a damaged thermal barrier, the method including subjecting a part coated in a damaged thermal barrier to electrophoresis treatment, the part being made of an electrically conductive material, the damaged thermal barrier including a ceramic material and presenting at least one damaged zone that is to be repaired, the part being present in an electrolyte including a suspension of particles in a liquid medium, the ceramic coating being deposited by electrophoresis in the damaged zone in order to obtain a repaired thermal barrier for use at temperatures higher than or equal to 1000&#xb0; C., the particles being made of a material different from the ceramic material present in the damaged thermal barrier.

Method for localised repair of a damaged thermal barrier

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Moissy-Cramayel, France

André Hubert Louis Malie