Thermal barrier coating formation method, thermal barrier coating, and high-temperature member

#The present invention relates to a thermal barrier coating formation method, a thermal barrier coating, and a high-temperature member.

#Priority is claimed on Japanese Patent Application Nos. 2017-087472 and 2017-087471, filed Apr. 26, 2017, the contents of which are incorporated herein by reference.

#To improve efficiency of a gas turbine, a temperature of a gas to be used is set to be high. A thermal barrier coating (TBC) is applied to surfaces of turbine members such as blades or vanes exposed to such a high-temperature gas. The thermal barrier coating is for coating the surface of the turbine member that is an object to be thermally sprayed with a thermal spraying material having a low thermal conductivity (e.g., a ceramic-based material having a low thermal conductivity) by means of thermal spraying. The thermal barrier coating is formed on the surface, and thereby a temperature of the high-temperature member exposed under a high-temperature high-pressure environment falls, and durability of the high-temperature member is improved.

#FIG. 1 is a schematic constitutional view of a gas turbine according to an embodiment of the present invention.

#FIG. 2 is a schematic constitutional perspective view of a blade according to an embodiment of the present invention.

#FIG. 3 is an enlarged sectional view of key parts of the blade for illustrating a thermal barrier coating according to an embodiment of the present invention.

#Hereinafter, an embodiment of the present invention will be described with reference to FIGS. 1 to 7.

#As illustrated in FIG. 1, a gas turbine 1 of the present embodiment includes a compressor 2, combustors 3, a turbine main body 4, and a rotor 5. A large quantity of air is introduced into the inside of the compressor 2, and is compressed. The combustors 3 mix a fuel with the compressed air A that is compressed by the compressor 2, and burn the mixture.

#The turbine main body 4 converts thermal energy of a combustion gas G introduced from the combustors 3 into rotational energy. The turbine main body 4 blows the combustion gas G to blades 7 provided on the rotor 5, thereby converting the thermal energy of the combustion gas G into mechanical rotational energy and generating power. In addition to the plurality of blades 7 close to the rotor 5 of the turbine main body 4, a plurality of vanes 8 are provided in a casing 6 of the turbine main body 4. In the turbine main body 4, the blades 7 and the vanes 8 are alternately arranged in an axial direction of the rotor 5. The rotor 5 transmits some of the rotating power of the turbine main body 4 to the compressor 2, and rotates the compressor 2.