The highest temperature of turbine entrance of the latest large-sized and highly efficient jet engine rises to more than 1773K. The TBC coating receives heat stress, mechanical stress, and according to combustion gas the coating is suffered corrosion damage etc during the operation. Therefore, TBC coating becomes indispensable and longer service life and higher heat resistant coating systems are strongly required. This paper employs a ternary coating system. The bond coating was vacuum plasmas sprayed NiCrAlY, and PSZ top coating was sprayed by an APS process. The molybdenum disilicide-metal composite coating was applied as middle coating. It is expected that the middle molybdenum disilicide layer can interrupt oxidation of NiCrAlY bond coating, therefore, extension of service life of TBC coating can be expected. Paper includes a German-language abstract.