High Temperature Components With Thermal Barrier Coatings for Gas Turbine

Abstract

The most principal feature of the present invention is as follows: Namely, in the gas-turbine-use high-temperature component including the thermal barrier coating and a cooling structure, micro passages are provided inside an alloy bond-coat layer and a thermal-barrier ceramic top-coat layer of the thermal barrier coating, the micro passages being in communication from the substrate side to the surface side. Moreover, a partial amount of coolant of a coolant for cooling the high-temperature component is caused to flow out to the outside of the high-temperature component via these micro passages. The employment of the structure like this makes it possible to expect the implementation of a high-temperature component's heat-resistant-temperature enhancement effect based on the transpiration cooling effect.

1 . A gas-turbine-use high-temperature component, comprising:
 a thermal barrier coating;   said thermal barrier coating being formed by providing an alloy bond-coat layer on a substrate surface exposed to a high-temperature combustion gas, and further, by providing a thermal-barrier ceramic top-coat layer on the surface of said alloy bond-coat layer, wherein   micro passages are provided inside said alloy bond-coat layer and said thermal-barrier ceramic top-coat layer, said micro passages being in communication from said substrate side to said surface side, a partial amount of coolant of a coolant for cooling said high-temperature component being caused to flow out to the outside of said high-temperature component via these micro passages.   
     
     
         2 . The gas-turbine-use high-temperature component according to  claim 1 , wherein
 said substrate is composed of a heat-resistant alloy of Ni-base, Co-base, or Fe-base.   
     
     
         3 . The gas-turbine-use high-temperature component according to  claim 1 , wherein
 said alloy bond-coat layer is composed of a MCrAlY (M is at least one species selected from Fe, Ni, and Co) alloy.   
     
     
         4 . The gas-turbine-use high-temperature component according to  claim 1 , wherein
 said alloy bond-coat layer is equipped with an accumulated organization of alloy powder particles, the particle diameters' range of said alloy powder particles being a 5 μm to 100 μm range,   the in-coating-film volume's partial ratio of said micro passages being equal to 30% to 70%, said micro passages being formed by clearances among said accumulated particles, and being in communication.   
     
     
         5 . The gas-turbine-use high-temperature component according to  claim 1 , wherein
 said alloy bond-coat layer is formed using a method of causing alloy powder particlesto collide with said substrate surface at a high velocity, and without being accompanied by the melting of said alloy powder particles,   said alloy powder particles being caused to collide with said substrate surface by accelerating said particles with an action gas whose temperature is lower than the melting point of said alloy.   
     
     
         6 . The gas-turbine-use high-temperature component according to  claim 1 , wherein
 said thermal-barrier ceramic top-coat layer is formed of partially-stabilized zirconia.   
     
     
         7 . The gas-turbine-use high-temperature component according to  claim 1 , wherein
 said micro passages of said thermal-barrier ceramic top-coat layer are formed of cracks.   
     
     
         8 . The gas-turbine-use high-temperature component according to  claim 1 , wherein
 said micro passages of said thermal-barrier ceramic top-coat layer are formed of pores.   
     
     
         9 . A gas turbine, comprising: said gas-turbine-use high-temperature component as claimed in  claim 1 . 
     
     
         10 . A gas-turbine-combined power-generation plant, comprising: said gas turbine as claimed in  claim 9 .