Snecma

Centre National De La Recherche Scientifique

Safran Aircraft Engines

Institut National Polytechnique De Toulouse

Université Paul Sabatier (toulouse Iii)

Universite Paul Sabatier De Toulouse

Universite Paul Sabatier Toulouse III - Upst III

Juliette Hugot

Claude Estournes

Daniel Monceau

Djar Oquab

Mathieu Boidot

Justine Menuey

Sarah Hamadi

Fabrice Crabos

Frederic Lagrange

Herve Molet

Franck Bourdin

Thierry Fevrier

Jerome Gestin

Jérôme Gestin

Frédéric Lagrange

Hervé Molet

André Hubert Louis Malie

The object of the present invention is to produce a metal part equipped with a protection system, particularly for turbine blades for aircraft engines, having a thermal barrier that is improved in terms of thermal properties, adhesion to the part and resistance to oxidation/corrosion. In order to achieve this, the method according to the invention produces in a single step, from specific ceramics, coating layers using SPS technology. According to one embodiment, a metal part is produced according to an SPS flash sintering method and comprises a superalloy substrate (), a metal sub-layer (), a TGO oxide layer () and the thermal barrier () formed by said method from at least two chemically and thermally compatible ceramic layers (). A first ceramic (), referred to as the inner ceramic, is designed to have a substantially higher expansion coefficient. The outer ceramic () is designed to have at least lower thermal conductivity, and a sintering temperature and/or maximum operating temperature that is substantially higher. The thermal barrier () has a composition and porosity gradient () from the metal sub-layer () to the outer ceramic ().

Process for producing a thermal barrier in a multilayer system for protecting a metal part and part equipped with such a protective system

A method for producing a thermal barrier in a multilayered system for protecting a metal part made of superalloy, by producing a thermal treatment by flash sintering protection materials in layers superposed on the metal part in an SPS machine enclosure. The layers contain, on a superalloy substrate, at least two layers of zirconium-based refractory ceramics. A metal part is produced according to a SPS flash sintering method and contains a superalloy substrate, a metal sub-layer, a TGO oxide layer and the thermal barrier formed by the method. A first ceramic is an inner ceramic designed to have a substantially higher expansion coefficient. An outer ceramic is designed to have at least lower thermal conductivity, and at least one of a sintering temperature or maximum operating temperature that is substantially higher. The thermal barrier has a composition and porosity gradient from the metal sub-layer to the outer ceramic.

The invention relates to a method of fabricating a bath of electrolyte for plating a platinum-based metal underlayer on a metallic substrate, comprising:

Method of fabricating a bath of electrolyte for plating a platinum-based metallic underlayer on a metallic substrate

A method for cleaning a turboshaft engine blade comprising a superalloy body covered with a coating, in which the coating of the blade is at least partially machined using a pulsed laser. At least the feed rate of the pulsed laser and the pulse frequency of the pulsed laser are parameterized such that the machined surface of the blade has a roughness of 4 &#x3bc;m to 10 &#x3bc;m.

Method for cleaning and stripping a turboshaft engine blade using a pulsed laser

A process and device in production of precise three-dimensional sinters of a shape substantially close to that of an original part, using flash sintering produced by spark plasma sintering (SPS) technology. A mold is produced in a die of an enclosure for SPS flash sintering, the mold being shaped as an impression of the original part. The following are deposited in successive layers in the mold: a layer based on a superalloy powder, a metallic protection layer, and a thermal barrier layer. In a sintering, pressurization is initiated and a pulsed current passes through, producing a rapid rise in temperature in accordance with a flash sintering cycle whose temperature, pressure, and duration are regulated, with at least one temperature plateau and one pressure plateau. The layer of superalloy forms, by diffusion, during the sintering, a bonding continuum of material with the part to be repaired.

Process for local repair of a damaged thermomechanical part and part thus produced, in particular a turbine part

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Jaunay-Clan, France

Juliette Hugot