Centre National De La Recherche Scientifique

Institut National Polytechnique De Toulouse

Safran Aircraft Engines

Snecma

Université Paul Sabatier (toulouse Iii)

Universite Paul Sabatier De Toulouse

Universite Paul Sabatier Toulouse III - Upst III

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