To coat a carbon-carbon compound material, for us in high temperature situations e.g. rocket turbines, the surface is coated by cementation followed by a silicon layer to be heated and impregnate the cracks

摘要

To coat the surfaces of a carbon/carbon compound material, as an oxygen barrier, the material surface is initially coated in a cementation process. The cladding is coated with silicon and the compound material is heated to give a silicon impregnation into the cladding cracks, at a temperature of 1400-1600[deg]C under a pressure of 1.332-133.32 Pa. The operation initially forms a SiC layer followed by a Si layer. The Si layer is oxidized at 400-800[deg]C to form a SiO 2 film. The total layer structure has a thickness of 10-2000 mu m.