Abstract: A seal member includes a ?? precipitation-hardening alloy, in which the ?? precipitation-hardening alloy has a component composition of, in mass %: Ni: from 40 to 62%; Cr: from 13 to 20%; Ti: from 1.5 to 2.8%; Al: from 1.0 to 2.0% (provided that Ti/Al: 2.0 or less); Nb: 2.0% or less; Ta: 2.0% or less (provided that Nb+Ta: from 0.2 to 2.0%); B: from 0.001 to 0.010%; W: 3.0% or less; and Mo: 2.0% or less (provided that Mo+(1/2)W: from 1.0 to 2.5%), and optionally, C: 0.08% or less; Si: 1.0% or less; Mn: 1.0% or less; P: 0.02% or less; and S: 0.01% or less, with the balance being Fe and inevitable impurities, and in which the seal member has a hardness of 250 Hv or more, and includes a cold-rolled microstructure obtained by a cold rolling.

Abstract: A component for a hot-dip metal plating bath includes a base material and a thermal spray coating disposed to cover a surface of the base material. The base material includes ferritic stainless steel that contains: C: 0.10% to 0.50% by mass; Si: 0.01% to 4.00% by mass; Mn: 0.10% by mass to 3.00% by mass; Cr: 15.0% to 30.0% by mass; a total of Nb, V, Ti, and Ta: 0.9% by mass to 5.0% by mass; and a balance of Fe and unavoidable impurities. The ferritic stainless steel includes a microstructure that includes a ferrite phase as a main phase and a crystallized carbide, an area fraction of a Nb carbide, a Ti carbide, a V carbide, a Ta carbide, and a composite carbide thereof to the crystallized carbide of 30% or more. The hot-dip metal plating bath contains 50% by mass or more of Al.

Abstract: A component for a hot-dip metal plating bath includes a base material and a thermal spray coating disposed to cover a surface of the base material. The base material includes ferritic stainless steel that contains: C: 0.10% to 0.50% by mass; Si: 0.01% to 4.00% by mass; Mn: 0.10% by mass to 3.00% by mass; Cr: 15.0% to 30.0% by mass; a total of Nb, V, Ti, and Ta: 0.9% by mass to 5.0% by mass; and a balance of Fe and unavoidable impurities. The ferritic stainless steel includes a microstructure that includes a ferrite phase as a main phase and a crystallized carbide, an area fraction of a Nb carbide, a Ti carbide, a V carbide, a Ta carbide, and a composite carbide thereof to the crystallized carbide of 30% or more. The component contains 50% by mass or more of Al.

Abstract: The present invention relates to an Ni-based superalloy having a composition containing, in terms of % by mass, C: from 0.1 to 0.3%, Cr: from 8.0 to 12.0%, Mo: from 1.0 to 5.0%, Co: from 10.0 to 20.0%, Ta: from 0.01 to 1.50%, Ti: from 2.0 to 4.2%, Al: from 5.0 to 8.0%, V: from 0 to 1.5%, B: from 0.005 to 0.030%, and Zr: from 0.05 to 0.15%, with the balance being Ni and unavoidable impurities, and satisfying, in terms of atom %, Ti+Al being from 16.0 to 20.3% and Ti/Al being 0.3 or less.

Abstract: The present invention relates to an Ni-based superalloy having a composition containing, in terms of % by mass, C: from 0.1 to 0.3%, Cr: from 8.0 to 12.0%, Mo: from 1.0 to 5.0%, Co: from 10.0 to 20.0%, Ta: from 0.01 to 1.50%, Ti: from 2.0 to 4.2%, Al: from 5.0 to 8.0%, V: from 0 to 1.5%, B: from 0.005 to 0.030%, and Zr: from 0.05 to 0.15%, with the balance being Ni and unavoidable impurities, and satisfying, in terms of atom %, Ti+Al being from 16.0 to 20.3% and Ti/Al being 0.3 or less.

Abstract: The present invention relates to a turbine wheel of an automotive turbocharger, including a Ni-based alloy having a composition which contains, in terms of mass %: C: 0.08 to 0.20%; Mn: 0.25% or less; Si: 0.01 to 0.50%; Cr: 12.0 to 14.0%; Mo: 3.80 to 5.20%; Nb+Ta: 1.80 to 2.80%; Ti: 0.50 to 1.00%; Al: 5.50 to 6.50%; B: 0.005 to 0.015%; Zr: 0.05 to 0.15%; and Fe: 0.01 to 2.5%, with the remainder being Ni and unavoidable impurities, in which the turbine wheel includes a wing part and a shaft part, and a size of ?? phase in each site of from a tip of the wing part to the shaft part is structure-controlled so as to fall within a range of from 0.4 to 0.8 ?m.

Abstract: The present invention relates to a Ti—Al-based heat-resistant member including a Ti—Al-based alloy which includes: 28.0 mass % to 35.0 mass % of Al; 1.0 mass % to 15.0 mass % of at least one selected from the group consisting of Nb, Mo, W and Ta; 0.1 mass % to 5.0 mass % of at least one selected from the group consisting of Cr, Mn and V; and 0.1 mass % to 1.0 mass % of Si, with the balance being Ti and unavoidable impurities, in which a whole or a part of a surface of the Ti—Al-based heat-resistant member includes a hardened layer as a surface layer, the hardened layer having a higher hardness than an inside of the Ti—Al-based heat-resistant member, and the Ti—Al-based heat-resistant member has a hardness ratio (a hardness of the surface layer/a hardness of the inside) of 1.4 to 2.5.

Abstract: The present invention relates to a Ti—Al-based heat-resistant member including a Ti—Al-based alloy which includes: 28.0 mass % to 35.0 mass % of Al; 1.0 mass % to 15.0 mass % of at least one selected from the group consisting of Nb, Mo, W and Ta; 0.1 mass % to 5.0 mass % of at least one selected from the group consisting of Cr, Mn and V; and 0.1 mass % to 1.0 mass % of Si, with the balance being Ti and unavoidable impurities, in which a whole or a part of a surface of the Ti—Al-based heat-resistant member includes a hardened layer as a surface layer, the hardened layer having a higher hardness than an inside of the Ti—Al-based heat-resistant member, and the Ti—Al-based heat-resistant member has a hardness ratio (a hardness of the surface layer/a hardness of the inside) of 1.4 to 2.5.

Abstract: The present invention relates to a turbine wheel of an automotive turbocharger, including a Ni-based alloy having a composition which contains, in terms of mass %: C: 0.08 to 0.20%; Mn: 0.25% or less; Si: 0.01 to 0.50%; Cr: 12.0 to 14.0%; Mo: 3.80 to 5.20%; Nb+Ta: 1.80 to 2.80%; Ti: 0.50 to 1.00%; Al: 5.50 to 6.50%; B: 0.005 to 0.015%; Zr: 0.05 to 0.15%; and Fe: 0.01 to 2.5%, with the remainder being Ni and unavoidable impurities, in which the turbine wheel includes a wing part and a shaft part, and a size of ?? phase in each site of from a tip of the wing part to the shaft part is structure-controlled so as to fall within a range of from 0.4 to 0.8 ?m.