A gas turbine blade thermal barrier coating bonding layer is composed of powdery Co, Ni, Cr, Al and Y. The optimal range of the powder particle size is 10-50 micrometers. A preparation method comprises the steps that 1, oil removal, washing and drying are performed on the surface of a matrix before spraying is performed, 40-80-mesh corundum is used for sand-blasting roughening, and floating dust is removed to form the rough surface; 2, the powder forming the bonding layer is kept at the temperature of 200-300 DEG C for 4 h before spraying is performed, and the powder is sufficiently softened; 3, a cold spraying method is adopted for preparing the bonding layer on the surface of the matrix; 4, the surface of the bonding layer is sprayed through the plasma technology to obtain an 8YSZ ceramic surface layer; 5, a complete thermal barrier coating is kept at the temperature of 900-1100 DEG C in a vacuum heat treatment furnace for 4 h, and the vacuum degree is lower than 10<-3>Pa. The technology is simple and low in cost; the porosity of the bonding layer is controlled to be smaller than 1%, and the structure is compact; pressure stress exists inside the coating, and the thermal expansion matching in the coating service process can be relieved; the bonding strength of the coating is improved, and the oxidation resistance of the coating is improved.