| abstract |
The present invention aims at producing a metal part equipped with a protection system, in particular for an aircraft engine turbine blade, having an improved thermal barrier in terms of thermal properties, adhesion to the workpiece and holding resistance. oxidation / corrosion. To do this, the method of the invention produces, from particular ceramics, coating layers according to the SPS technology in a single step. According to one embodiment, a metal part is made according to an SPS flash sintering method and comprises a superalloy substrate (22), a metal underlayer (21), a TGO oxide layer (25), and the barrier thermal device (23) formed by said method from at least two ceramic layers (2a, 2b), chemically and thermally compatible. A first ceramic (2a), called internal, is able to have a substantially higher coefficient of expansion. The outer ceramic (2b) is able to have at least a lower thermal conductivity, a sintering temperature and / or a significantly higher limit temperature of use. The thermal barrier (23) has a compositional gradient, porosity (3) from the metal sub-layer (21) to the outer ceramic (2b). |