Abstract: Provided is a Ni-based single crystal superalloy containing 6% by mass or more and 12% by mass or less of Cr, 0.4% by mass or more and 3.0% by mass or less of Mo, 6% by mass or more and 10% by mass or less of W, 4.0% by mass or more and 6.5% by mass or less of Al, 0% by mass or more and 1% by mass or less of Nb, 8% by mass or more and 12% by mass or less of Ta, 0% by mass or more and 0.15% by mass or less of Hf, 0.01% by mass or more and 0.2% by mass or less of Si, and 0% by mass or more and 0.04% by mass or less of Zr, and optionally containing at least one element selected from B, C, Y, La, Ce, and V, with a balance being Ni and inevitable impurities.

Abstract: An alloy material having high-temperature corrosion resistance, which exhibits excellent oxidation resistance and ductility and can be applied to gas turbines used at ultra high temperatures, and a thermal barrier coating, a turbine member and a gas turbine each comprising the alloy material. An alloy material having high-temperature corrosion resistance, comprising, by weight, Co: 15 to 30%, Cr: 10 to 30%, Al: 4 to 15%, Y: 0.1 to 3%, and Re: 0.1 to 1%, with the balance being substantially Ni. Also, an alloy material having high-temperature corrosion resistance, comprising, by weight, Ni: 20 to 40%, Cr: 10 to 30%, Al: 4 to 15%, Y: 0.1 to 3%, and Re: 0.1 to 5%, with the balance being substantially Co.

Abstract: In a specimen collecting method according to the present invention, a specimen is collected from a surface (114a) of a blade. An ultrasonic cutter having a cylindrical cutting blade is fed from the surface (114a) of the blade to a surface (110a) of a base material (100), and thus, a cylindrical incision is formed. After performing cutting to expand the incision outwardly, a rotating cutter (220) having a disc-shaped cutting blade (222) performs cutting inwardly from the cylindrical incision. Thus, a part (20a) situated inside the incision is cut away. The part (20a) becomes the specimen.

Abstract: An alloy material having high-temperature corrosion resistance, which exhibits excellent oxidation resistance and ductility and can be applied to gas turbines used at ultra high temperatures, and a thermal barrier coating, a turbine member and a gas turbine each comprising the alloy material. An alloy material having high-temperature corrosion resistance, comprising, by weight, Co: 15 to 30%, Cr: 10 to 30%, Al: 4 to 15%, Y: 0.1 to 3%, and Re: 0.1 to 1%, with the balance being substantially Ni. Also, an alloy material having high-temperature corrosion resistance, comprising, by weight, Ni: 20 to 40%, Cr: 10 to 30%, Al: 4 to 15%, Y: 0.1 to 3%, and Re: 0.1 to 5%, with the balance being substantially Co.

Abstract: In a specimen collecting method according to the present invention, a specimen is collected from a surface (114a) of a blade. An ultrasonic cutter having a cylindrical cutting blade is fed from the surface (114a) of the blade to a surface (110a) of a base material (100), and thus, a cylindrical incision is formed. After performing cutting to expand the incision outwardly, a rotating cutter (220) having a disc-shaped cutting blade (222) performs cutting inwardly from the cylindrical incision. Thus, a part (20a) situated inside the incision is cut away. The part (20a) becomes the specimen.

Abstract: The present invention provides an oxidation-resistant coating having superior oxidation resistance and superior ductility and toughness for long-term use, and a method for forming the oxidation-resistant coating. An MCrAlY layer primarily containing an MCrAlY alloy (in which M indicates at least one element of Co and Ni) is formed on a substrate formed of a heat-resistant metal by thermal spraying or EB=PVD, and subsequently, aluminum is diffused into a part of the MCrAlY layer in the thickness direction thereof from a side opposite to the substrate.

Abstract: The present invention provides an oxidation-resistant coating having superior oxidation resistance and superior ductility and toughness for long-term use, and a method for forming the oxidation-resistant coating. An MCrAlY layer primarily containing an MCrAlY alloy (in which M indicates at least one element of Co and Ni) is formed on a substrate formed of a heat-resistant metal by thermal spraying or EB=PVD, and subsequently, aluminum is diffused into a part of the MCrAlY layer in the thickness direction thereof from a side opposite to the substrate.

Abstract: Disclosed is a Ni-based sintered alloy used for preparing a high temperature part utilized under a high temperature gas atmosphere, characterized in that the Ni-based sintered alloy is prepared by mixing and heating two kinds of Ni alloy powders differing from each other in the melting point.

Abstract: Disclosed is a Ni-based sintered alloy used for preparing a high temperature part utilized under a high temperature gas atmosphere, characterized in that the Ni-based sintered alloy is prepared by mixing and heating two kinds of Ni alloy powders differing from each other in the melting point.

Abstract: Disclosed is a Ni-based sintered alloy used for preparing a high temperature part utilized under a high temperature gas atmosphere, characterized in that the Ni-based sintered alloy is prepared by mixing and heating two kinds of Ni alloy powders differing from each other in the melting point.

Abstract: Disclosed is a Ni-based sintered alloy used for preparing a high temperature part utilized under a high temperature gas atmosphere, characterized in that the Ni-based sintered alloy is prepared by mixing and heating two kinds of Ni alloy powders differing from each other in the melting point.

Abstract: A high temperature corrosion resistant alloy composition comprising, in addition to Ni, 0.1 to 12% by weight of Co, 10 to 30% by weight of Cr, 4 to 15% by weight of Al, 0.1 to 5% by weight of Y, and 0.5 to 10% by weight of Re. The high temperature corrosion resistant alloy composition has an excellent oxidation resistance and ductility and is suitable for use in a bonding layer of a thermal barrier coating material.

Abstract: A high temperature corrosion resistant alloy composition comprising, in addition to Ni, 0.1 to 12% by weight of Co, 10 to 30% by weight of Cr, 4 to 15% by weight of Al, 0.1 to 5% by weight of Y, and 0.5 to 10% by weight of Re. The high temperature corrosion resistant alloy composition has an excellent oxidation resistance and ductility and is suitable for use in a bonding layer of a thermal barrier coating material.