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AssigneesSafran Aircraft Engines, Centre National De La Recherche Scientifique, Institut National Polytechnique De Toulouse, Universite Paul Sabatier De Toulouse
InventorsJuliette Hugot, Mathieu Boidot, Daniel Monceau, Djar Oquab, Claude Estournes
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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 (22), a metal sub-layer (21), a TGO oxide layer (25) and the thermal barrier (23) formed by said method from at least two chemically and thermally compatible ceramic layers (2a, 2b). A first ceramic (2a), referred to as the inner ceramic, is designed to have a substantially higher expansion coefficient. The outer ceramic (2b) 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 (23) has a composition and porosity gradient (3) from the metal sub-layer (21) to the outer ceramic (2b).
A metal part made of superalloy, equipped with a thermal barrier being formed by a flash sintering operation in an SPS machine enclosure,
A metal part made of superalloy and comprising an assembly of layers of material comprising:
Dependencies are inferred from the claim text.