Centre National De La Recherche Scientifique

Institut National Polytechnique De Toulouse

Safran Aircraft Engines

Université Paul Sabatier (Toulouse III)

Snecma

Daniel Monceau

Claude Estournes

Mathieu Boidot

Djar Oquab

Juliette Hugot

Serge Selezneff

Jean-yves Guedou

Jean-Claude Salabura

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 part comprising a coating on a superalloy metal substrate, the coating comprising a metal underlayer covering said substrate, the part being characterized in that said metal underlayer contains a base of nickel aluminide and also contains 0.5 at % to 0.95 at % of one or more stabilizer elements M from the group formed by Cu and Ag for stabilizing the gamma and gamma prime phases.

Part comprising a coating on a superalloy metal substrate, the coating including a metal underlayer

A method for thermogravimetrically testing the behavior of a solid material in the presence of a controlled gaseous atmosphere, characterized in that a plurality of samples () are placed in the presence of the gaseous atmosphere inside the same controlled atmosphere furnace (); each sample is associated with a scale () proper thereto; the samples () undergo predetermined successive thermal cycles each including a heating step during which the samples are directly heated (by radiation or induction) and a cooling step during which the weight of each sample is independently measured and recorded in a continuous manner during at least one predetermined period such as a high temperature level during the heating step of each thermal cycle. The invention also relates to a device for carrying out the method.

Device and method for thermogravimetrically testing the behavior of a solid material

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Nailloux, France

Daniel Monceau