Gas turbine blade thermal barrier coating prepared through spraying method

The invention belongs to the technical field of thermal barrier coatings and particularly relates to a gas turbine blade thermal barrier coating prepared through a spraying method. The gas turbine blade thermal barrier coating comprises a high-temperature base body. The upper side of the high-temperature base body is coated with a diffusion layer. The upper side of the diffusion layer is coated with a bonding layer. The upper side of the bonding layer is coated with an oxidation film layer. The upper side of the oxidation film layer is coated with a ceramic layer. The bonding layer comprises Co, Ni, Cr, Al and Y metal powder or alloy powder. The preparation method comprises the steps of (1) conducting oil removal, water washing and drying on the surface of the high-temperature base body, conducting sand blasting and roughening treatment through 50-100 meshes of corundum, and removing floating dust to form a rough surface; (2) conducting temperature preservation on powder of the bondinglayer under 200-250 DEG