Thermal barrier coating, turbine member, gas turbine, and manufacturing method for thermal barrier coating

Abstract

A thermal barrier coating ( 100 ) includes a heat-resistant alloy substrate which is used in a turbine member and a ceramic layer ( 300 ) which is formed on the heat-resistant alloy substrate and in which vertical cracks (C) extending in a thickness direction are dispersed in a surface direction and a plurality of pores (P) are included on the inside. Thermal spray particles composed of YbSZ having a particle-size distribution in which a 50% particle diameter in a cumulative particle-size distribution is 40 μm to 100 μm are thermally sprayed at a thermal spray distance of 80 mm or less, the vertical cracks (C) are dispersed at a pitch of 0.5 cracks/mm to 40 cracks/mm in the surface direction, and the ceramic layer ( 300 ) of which a porosity attributable to the vertical cracks (C) and the pores (P) combined is 4% to 15% is formed.

1 - 5 . (canceled) 
     
     
         6 . A manufacturing method for a thermal barrier coating, comprising a ceramic layer forming process of forming a ceramic layer on a heat-resistant alloy substrate used in a turbine member by thermally spraying thermal spray particles composed of YbSZ having a particle-size distribution in which a 50% particle diameter in a cumulative particle-size distribution is 40 μm to 100 μm at a thermal spray distance of 80 mm or less, wherein in the ceramic layer, vertical cracks extending in a thickness direction are dispersed in a surface direction, wherein the vertical cracks are dispersed at a pitch of 0.5 cracks/mm to 40 cracks/mm in the surface direction, wherein a plurality of pores are included inside the ceramic layer, and wherein a porosity of the ceramic layer attributable to the vertical cracks and the pores combined is 4% to 15%. 
     
     
         7 . A manufacturing method for a thermal barrier coating, comprising a ceramic layer forming process of forming a ceramic layer on a heat-resistant alloy substrate used in a turbine member by thermally spraying thermal spray particles composed of YbSZ having a particle-size distribution in which a 50% particle diameter in a cumulative particle-size distribution is 40 μm to 100 μm at a thermal spray distance of 80 mm or less, wherein in the ceramic layer, vertical cracks extending in a thickness direction are dispersed in a surface direction, wherein the vertical cracks are dispersed at a pitch of 1 crack/mm to 6 cracks/mm in the surface direction, wherein a plurality of pores are included inside the ceramic layer, and wherein a porosity of the ceramic layer attributable to the vertical cracks and the pores combined is 9% to 15%. 
     
     
         8 . A manufacturing method for a thermal barrier coating, comprising a ceramic layer forming process of forming a ceramic layer on a heat-resistant alloy substrate used in a turbine member by thermally spraying thermal spray particles composed of YbSZ having a particle-size distribution in which a 50% particle diameter in a cumulative particle-size distribution is 40 μm to 100 μm at a thermal spray distance of 80 mm or less, wherein in the ceramic layer, vertical cracks extending in a thickness direction are dispersed in a surface direction, wherein the vertical cracks are dispersed at a pitch of 1 crack/mm to 2 cracks/mm in the surface direction, wherein a plurality of pores are included inside the ceramic layer, and wherein a porosity of the ceramic layer attributable to the vertical cracks and the pores combined is 9% to 10%.