Thermal coating useful in a thermomechanical part of e.g. a turbomachine and an aircraft engine, comprises a stack of two layers defining a plane and an orthogonal direction of the plane, and first and second thermal insulation layers

摘要

The thermal coating (30) comprises a stack of two layers defining a plane and an orthogonal direction of the plane, a first thermal insulation layer having a thermal conductivity of lower than 5 Wm ->1>K ->1>in the orthogonal direction and a second thermal insulation layer having an anisotropic thermal conductivity of greater than 500 Wm ->1>K ->1>parallel to the plane. The second thermal insulation layer comprises graphite, graphene sheets parallely superimposed to the plane, and carbon nanotubes whose main axis is parallely oriented to the plane. The thermal coating (30) comprises a stack of two layers defining a plane and an orthogonal direction of the plane, a first thermal insulation layer having a thermal conductivity of lower than 5 Wm ->1>K ->1>in the orthogonal direction and a second thermal insulation layer having an anisotropic thermal conductivity of greater than 500 Wm ->1>K ->1>parallel to the plane. The second thermal insulation layer comprises graphite, graphene sheets parallely superimposed to the plane, and carbon nanotubes whose main axis is parallely oriented to the plane. The first layer is a heat barrier system comprising a metallic undercoat layer overlaid in a ceramic layer. Platinum layers (18, 20) are placed at a distance from one another in the second insulation layer, and have a thickness of 2-5 mu m.