Abstract: A method of forming a sprayed coating includes preparing a spray target member having a surface on which openings of first ends of holes are formed, preparing a plurality of masking pins each of which comprises metal, and inserting each of the masking pins into a corresponding one of the holes so that each of the masking pins partially protrudes from the surface. The method also includes applying an adhesive agent for fixing the masking pins to the respective holes, to at least one of the holes or the masking pins, forming a ceramic layer by spraying on the surface of the spraying target member, the ceramic layer comprising a ceramic material, while the masking pins are fixed to the respective holes via the adhesive agent, and removing the masking pins from the holes after the spraying step.

Abstract: A steam turbine rotor blade for forming a turbine rotor cascade of a steam turbine includes a rotor blade main body having a blade portion, a blade base portion and a first coupling portion, which has first facing surfaces, provided on opposite end sides of the blade portion, and a second coupling portion provided in an intermediate portion of the blade portion and having second facing surfaces. The steam turbine rotor blade also includes a coating layer which is made of a Co-based alloy having a single composition on a surface of at least one of the first and second facing surfaces with a diffusion layer having a thickness of 10 ?m or less provided between the coating layer and the surface.

Abstract: A method for producing a turbine blade includes forming an undercoat on a surface of a base material of a turbine blade, which is formed of a Ni-based alloy material, the undercoat being formed of a metallic material having a higher oxidation-resisting property than that of the base material, performing diffusing treatment for heating the base material having the undercoat formed thereon and diffusing a part of the undercoat on the base material side, and forming a topcoat on a surface of the undercoat after the diffusing treatment is performed, the topcoat being formed of a material having a lower thermal conductivity than that of the base material and the undercoat.

Abstract: A method for producing a turbine blade includes performing brazing treatment, performing annealing, and subjecting a base material to solutionizing treatment. In the brazing treatment, a brazing material is welded to be joined to the base material of a turbine blade by operating a heater to perform heating at a first temperature under a state in which the base material having the brazing material arranged thereon is placed in a predetermined heating furnace including the heater. In annealing, the base material is cooled by stopping the heater and lowering a furnace internal temperature after the brazing treatment. In the solutionizing treatment, ductility of the base material is improved through heating at a second temperature lower than the first temperature after the annealing.

Abstract: A method for producing a thermal spray powder includes: a preparing step of preparing a powder mixture containing a first particle made from zirconia-based ceramic containing a first additive agent and a second particle made from zirconia-based ceramic containing a second additive agent, the powder mixture having a 10% cumulative particle diameter of more than 0 ?m and not more than 10 ?m; and a secondary-particle producing step of producing a plurality of secondary particles each of which includes the first particle and the second particle sintered with each other.

Abstract: An erosion test apparatus includes a combustor configured to obtain a combustion gas by mixing and combusting compressed air and a fuel, and an erodent supply unit configured to supply an erodent to the combustion gas. The erosion test apparatus further includes an accommodation support unit configured to accommodate and support a test piece having a front surface coated through thermal barrier coating, and an accelerator configured to accelerate the combustion gas including the erodent to collide with the test piece.

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 ?m to 100 ?m 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.

Abstract: The present invention provides a production method for thermal spray particles forming a ceramic layer in which vertical cracks extending in a thickness direction are dispersed in a surface direction and which includes a plurality of pores inside. The production method for thermal spray particles includes adjusting a solid content concentration of slurry (13) to 75 wt % to 85 wt %, supplying the slurry (13) to a disk-shaped atomizer (12) of a spray drying device (10), setting a protrusion speed at which the slurry (13) protrudes from the atomizer (12) to 60 m/second to 90 m/second. and performing a heat treatment on thermal spray particle bodies (22) formed by drying the slurry (13) to produce thermal spray particles composed of YbSZ in which a 50% particle diameter in a cumulative particle-size distribution is 40 ?m to 100 ?m.

Abstract: A method of forming a sprayed coating includes preparing a spray target member having a surface on which openings of first ends of holes are formed, preparing a plurality of masking pins each of which comprises metal, and inserting each of the masking pins into a corresponding one of the holes so that each of the masking pins partially protrudes from the surface. The method also includes applying an adhesive agent for fixing the masking pins to the respective holes, to at least one of the holes or the masking pins, forming a ceramic layer by spraying on the surface of the spraying target member, the ceramic layer comprising a ceramic material, while the masking pins are fixed to the respective holes via the adhesive agent, and removing the masking pins from the holes after the spraying step.

Abstract: A steam turbine rotor blade for forming a turbine rotor cascade of a steam turbine includes a rotor blade main body having a blade portion, a blade base portion and a first coupling portion, which has first facing surfaces, provided on opposite end sides of the blade portion, and a second coupling portion provided in an intermediate portion of the blade portion and having second facing surfaces. The steam turbine rotor blade also includes a coating layer which is made of a Co-based alloy having a single composition on a surface of at least one of the first and facing surfaces with a diffusion layer having a thickness of 10 ?m or less provided between the coating layer and the surface.

Abstract: A method for producing a thermal spray powder includes: a preparing step of preparing a powder mixture containing a first particle made from zirconia-based ceramic containing a first additive agent and a second particle made from zirconia-based ceramic containing a second additive agent, the powder mixture having a 10% cumulative particle diameter of more than 0 ?m and not more than 10 ?m; and a secondary-particle producing step of producing a plurality of secondary particles each of which includes the first particle and the second particle sintered with each other.

Abstract: A heat shielding coating (11) includes a bond coat layer (12) as a metal coupling layer laminated on a base material (10), and a top coat layer (13) which is laminated on the bond coat layer (12) and includes zirconia-based ceramic, in which the top coat layer (13) has a porosity of 9% or less.

Abstract: An erosion test apparatus includes a combustor configured to obtain a combustion gas by mixing and combusting compressed air and a fuel, and an erodent supply unit configured to supply an erodent to the combustion gas. The erosion test apparatus further includes an accommodation support unit configured to accommodate and support a test piece having a front surface coated through thermal barrier coating, and an accelerator configured to accelerate the combustion gas including the erodent to collide with the test piece.