▎ 摘　　要

NOVELTY - Thermal barrier coating comprises high-temperature alloy substrate to be processed from bottom to top, bonding layer, ceramic layer, yttrium oxide-graphene composite coating or zirconium oxide-tungsten composite coating. The surface of the ceramic layer is provided with a micron-sized mastoid array structure. USE - Thermal barrier coating with anti-CMAS erosion for use in an aircraft engine, gas turbine engine and a water turbine engine. ADVANTAGE - The thermal barrier coating has excellent anti-CMAS erosion property, anti-corrosion performance, and stability, and prevents the fused CMAS attached on the surface of the ceramic layer, thus improving the anti- CMAS erosion ability of the thermal barrier coatings. DETAILED DESCRIPTION - An INDEPENDENT CLAIM is included for the method for preparing thermal barrier coating with anti-calcium oxide, magnesium oxide, a mixture of aluminum oxide and silicon oxide (CMAS) erosion, which involves: 1. preparing the micron mastoid array structure with diameter of 10-120 microns, height of 20-50 microns and distance of 30-120 microns on the surface of the thermal barrier coating ceramic layer, or the bonding layer surface preparation diameter is 10-120 microns the height is 20-50 microns, the distance is 30-120 microns of micron mastoid array structure; 2. preparing thermal barrier coating ceramic layer the heat barrier coating ceramic layer surface also obtains the micron mastoid array structure; 3. using dip coating or rotary coating method to uniformly coat the yttrium oxide-graphene or zirconium oxide-graphene dispersion on the surface of the ceramic layer in 10-3000nm, the thickness of the coating is extending the obtained yttrium oxide-graphene or zirconium oxide-graphene coating surface to obtain the micron mastoid array structure; and 4. putting the sample coated into a drying box to dry.