Abstract: A thermal barrier coating film includes a bond coat layer that is a metallic bond layer formed on a base material; a topcoat layer that is a ceramic-containing layer formed on the bond coat layer; and at least one of a protective layer and a protective substance. The protective layer is formed on the topcoat layer and mainly containing SrSO4. The protective substance is provided in the interior of a plurality of void spaces included in the topcoat layer and mainly contains SrSO4.

Abstract: A coating apparatus is provided that includes: a mixer configured to generate mixed ceramic powder in which a material which contains an organic compound imparting lubricity to raw ceramic powder whose average particle size is smaller than or equal to 10 ?m and acts as an additive is mixed into the raw ceramic powder; a jetting device configured to jet the mixed ceramic powder toward a surface of a base material; and a heating device configured to heat the mixed ceramic powder jetted from the jetting device, and to evaporate the organic compound of the additive contained in the mixed ceramic powder.

Abstract: A thermal barrier coating includes a highly porous layer and a dense layer. The highly porous layer is formed on a heat-resistant base, is made of ceramic, has pores, has a layer thickness of equal to or larger than 0.3 mm and equal to or smaller than 1.0 mm, and has a pore ratio of equal to or higher than 1 vol % and equal to or lower than 30 vol %. The dense layer is formed on the highly porous layer, is made of ceramic, has a pore ratio of equal to or lower than 0.9 vol % that is equal to or lower than the pore ratio of the highly porous layer, and has a layer thickness of equal to or smaller than 0.05 mm.

Abstract: A member joining method is for joining a first member with a second member by welding. The method includes performing welding of the first member and the second member from a side of high-temperature use environmental surfaces of the first member and the second member under a condition in which the first member abuts on the second member through hooked portions, each hooked portion being provided on an abutment surface, on which the first member and the second member under abutting, of each of the first member and the second member.

Abstract: A method for repairing a target member including a ceramic matrix composite reinforced by ceramic fiber includes: a removal step of removing at least a part of a surface of the target member; an arrangement step of arranging a green body for repair which includes the ceramic fiber on a portion where the surface is removed in the removal step; an impregnation step of impregnating at least the portion of the target member where the green body for repair is disposed with slurry; and a sintering step of sintering the target member on which the green body for repair is disposed, after the impregnation step.

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 process for producing a thermal barrier coating having an excellent thermal barrier effect and superior durability to thermal cycling. Also, a turbine member having a thermal barrier coating that has been formed using the production process, and a gas turbine. The process for producing a thermal barrier coating includes: forming a metal bonding layer (12) on a heat-resistant alloy substrate (11), and forming a ceramic layer (13) on the metal bonding layer (12) by thermal spraying of thermal spray particles having a particle size distribution in which the 10% cumulative particle size is not less than 30 ?m and not more than 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 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.

Abstract: It is an object to provide a repairing method for a wall member with flow passages capable of reducing the time and the cost required for a partial repairing work on the wall member with flow passages. The repairing method for the wall member with flow passages includes a removal stage of removing a portion of the wall member with flow passages (1) provided with plural flow passages (4) between the base member (2) and the plate member (3), the base member welding stage of welding the repairing base member (6) to the portion removed in the removal stage, a flow passage forming stage of providing plural overlay welds on the repairing base member (6) and forming the flow passages (4) between the overlay welded beads (8), and a plate member welding stage of welding a repairing plate member (9) onto surfaces of the plural overlay welded beads (8).

Abstract: A turbine rotor blade repair method which reduces the occurrence of cracks due to welding is provided. A turbine rotor blade repair method for repairing damage of a fin at a tip of a turbine rotor blade includes overlaying a damaged portion of the fin with metal by welding (step S2); peening on a boundary region between the fin and the overlaying metal (step S4); and after the peening, performing solution treatment to repair the damage of the fin of the turbine rotor blade (step S6).

Abstract: A process for producing a thermal barrier coating having an excellent thermal barrier effect and superior durability to thermal cycling. Also, a turbine member having a thermal barrier coating that has been formed using the production process, and a gas turbine. The process for producing a thermal barrier coating includes: forming a metal bonding layer (12) on a heat-resistant alloy substrate (11), and forming a ceramic layer (13) on the metal bonding layer (12) by thermal spraying of thermal spray particles having a particle size distribution in which the 10% cumulative particle size is not less than 30 ?m and not more than 100 ?m.

Abstract: It is an object to provide a repairing method for a wall member with flow passages capable of reducing the time and the cost required for a partial repairing work on the wall member with flow passages. The repairing method for the wall member with flow passages includes a removal stage of removing a portion of the wall member with flow passages (1) provided with plural flow passages (4) between the base member (2) and the plate member (3), the base member welding stage of welding the repairing base member (6) to the portion removed in the removal stage, a flow passage forming stage of providing plural overlay welds on the repairing base member (6) and forming the flow passages (4) between the overlay welded beads (8), and a plate member welding stage of welding a repairing plate member (9) onto surfaces of the plural overlay welded beads (8).

Abstract: A turbine rotor blade repair method which reduces the occurrence of cracks due to welding is provided. A turbine rotor blade repair method for repairing damage of a fin at a tip of a turbine rotor blade includes overlaying a damaged portion of the fin with metal by welding (step S2); peening on a boundary region between the fin and the overlaying metal (step S4); and after the peening, performing solution treatment to repair the damage of the fin of the turbine rotor blade (step S6).

Abstract: A welding method forms a molten build-up portion on a base material that is any one of a single crystal material and a unidirectionally solidified crystal material. The method includes forming a plurality of build-up portions on the base material while maintaining a predetermined gap between adjacent build-up portions; and forming a build-up portion in each of the predetermined gaps.

Abstract: When a three-dimensional structure is formed by welding a plurality of members, accurate welding can be performed matching the three-dimensional shape. The teaching data consisting of the three-dimensional position at each of the welding points determined on each of the welding lines at a predetermined spacing on the basis of the design data of the three-dimensional structure is stored in a memory 18. A laser slit light sensor (a laser slit light emitting section 12 and a CD camera 13) is controlled by a total controller 17 via a camera controller 14 to photograph the welding point in order to obtain the image data of the welding point. An image processing apparatus 16 processes the image data to determine the amount of deviation from the design data of welding points.

Abstract: A brazing filler metal sheet is prepared. The brazing filler metal sheet includes a brazing filler metal layer, a sticking material layer, and a released paper. The brazing filler metal layer includes a brazing filler metal. A coating material layer is laminated on the brazing filler metal layer. The coating material layer includes a mixture of coating material particles and a binder. As the coating material particles, MCrAlY particles and abrasive particles are used. The coating material layer is then dried, and the brazing filler metal sheet is cut (step S4), and adhered to a rotor blade. The rotor blade is heated, to melt the brazing filler metal. The brazing filler metal diffuses due to the heat treatment holding process. A solidified layer is then formed by cooling. This solidified layer is subjected to blasting to allow the cubic boron nitride particles to protrude.