Abstract: A method of manufacturing a turbine blade includes a brazing treatment for joining a brazing material to a base material of a turbine blade by heating the base material having the brazing material arranged thereon and melting the brazing material, a stabilizing treatment for heating the base material having been subjected to the brazing treatment; and an aging treatment for heating the base material having been subjected to the stabilizing treatment. The brazing treatment and the stabilizing treatment are performed with a sequential heating treatment.

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 of manufacturing a turbine blade includes brazing treatment for joining a brazing material to a base material of a turbine blade by heating the base material having the brazing material arranged thereon and melting the brazing material, stabilizing treatment for heating the base material having been subjected to the brazing treatment; and aging treatment for heating the base material having been subjected to the stabilizing treatment. The brazing treatment and the stabilizing treatment are performed with one heating treatment.

Abstract: A low thermal expansion Ni-base superalloy contains, by weight % (hereinafter the same as long as not particularly defined) C: 0.15% or less; Si: 1% or less; Mn: 1% or less; Cr: 5 to 20%; at least one of Mo, W and Re of Mo+½(W+Re) of 17 (exclusive) to 25%; Al: 0.2 to 2%; Ti: 0.5 to 4.5%; Fe of 10% or less; at least one of B: 0.02% and Zr: 0.2% or less; a remainder of Ni and inevitable impurities; wherein the atomic % of Al+Ti is 2.5 to 7.0.

Abstract: A low thermal expansion Ni-base superalloy contains, by weight % (hereinafter the same as long as not particularly defined) C: 0.15% or less; Si: 1% or less; Mn: 1% or less; Cr: 5 to 20%; at least one of Mo, W and Re of Mo+½ (W+Re) of 17 (exclusive) to 25%; Al: 0.2 to 2%; Ti: 0.5 to 4.5%; Fe of 10% or less; at least one of B: 0.02% and Zr: 0.2% or less; a remainder of Ni and inevitable impurities; wherein the atomic % of Al+Ti is 2.5 to 7.0.

Abstract: Provided is high temperature equipment, such as gas turbine high temperature portion, usable in high temperature corrosion environment due to corrosive components and in erosion environment due to flying particles. Coating layer (2) in which Cr3C2 is finely dispersed in matrix MCrAlY, where weight ratio of MCrAlY/Cr3C2 is 1/1 to 3/1, is formed on base material (1) as sprayed coating and then diffusion heat treatment is added.

Abstract: A high temperature corrosion-resistant and abrasion-resistant coated member or part which is suitable for use under a severe high temperature corrosive and severe abrasive environment and in flying particles, and a manufacturing method thereof are provided. A manufacturing method of a high temperature corrosion-resistant and abrasion-resistant coated member wherein an Al diffusion and infiltration treatment is performed after a chromium carbide coating has been applied onto the surface of a base material, or wherein a chromium carbide coating layer whose outside surface is an Al diffusion layer is formed on the surface of the base material, and a gas turbine blade comprising the above member are provided.

Abstract: An Ni-base heat resistant alloy, has a composition which contains, by weight, Cr: from 12.0 to 14.3%, Co: from 8.5 to 11.0%, Mo: from 1.0 to 3.5%, W: from 3.5 to 6.2%, Ta: from 3.0 to 5.5%, Al: from 3.5 to 4.5%, Ti: from 2.0 to 3.2%, C: from 0.04 to 0.12%, B: from 0.005 to 0.05%, and the balance substantially Ni and inevitable impurities. A large-size casting, as well as a large-size turbine blade, having a columnar crystalline Ni-base heat-resistant alloy formed from the Ni-base heat-resistant alloy, have sound cast surfaces and a sound internal structure.

Abstract: There is provided a property recovering method which can be applied to a high-temperature member whose properties such as strength and ductility have been deteriorated by the long-term use at a high temperature to recover its properties to those before the use, enable its reuse, and contribute to the effective use of resources and the conservation of environment. A Ni-base heat resistant alloy having a particular composition, whose properties have been deteriorated by heat history, is subjected to first-stage solution treatment, in which the alloy is held at a temperature of 1175 to 1225° C. for 1 to 5 hours and then furnace-cooled, then subjected to second-stage solution treatment, in which the alloy is held at a temperature of 1115 to 1165° C. for 1 to 5 hours and then air-cooled, and further subjected to aging treatment, in which the alloy is held at a temperature of 810 to 860° C. for 22 to 26 hours.

Abstract: Provided is a process for improving alloy properties which can improve the high-temperature ductility of a Ni-base heat-resisting alloy while maintaining its excellent high-temperature strength and weldability.

Abstract: A material for a gas turbine disk comprises 0.05 to 0.15 wt % of carbon, 0.10 wt % or less of silicon, 0.40 wt % or less of manganese, 9.0 to 12.0 wt % of chromium, 1.0 to 3.5 wt % of nickel, 0.50 to 0.90 wt % of molybdenum, 1.0 to 2.0 wt % of tungsten, 0.10 to 0.30 wt % of vanadium, 0.01 to 0.10 wt % of niobium, 0.01 to 0.05 wt % of nitrogen, and a remainder comprising iron and unavoidable impurities, wherein the contents of nickel, molybdenum and tungsten satisfy a relationship -1.5 wt %.ltoreq.Mo+W/2-Ni.ltoreq.0.7 wt %. Accordingly, unlike conventional gas turbine disk materials such as a heat resisting steel of 12Cr-type which can be used in an operation at about 400.degree. C., but has reduced toughness and high-temperature creep characteristics in an operation at about 500.degree. C., this material is allowed to have a satisfactory toughness and excellent high-temperature creep characteristics and can be suitably used at high temperatures.

Abstract: The present invention discloses ferritic heat resisting steels for manufacturing a rotor or a disk of a gas turbine, which have high creep rupture strength at high temperatures and excellent tenacity at room ordinary temperatures. The highly tenacious ferritic heat resisting steels contain, by weight, carbon of 0.08 to 0.25%, silicon of 0.5% or lower, manganese of 1.0% or lower, nickel exceeding 1.0% and lower than 3.0%, chromium of 9.0 to 12.5%, molybdenum exceeding 0.3% and lower than 1.5%, tungsten of 1.0 to 3.0%, vanadium of 0.10 to 0.35%, niobium of 0.02 to 0.10%, nitrogen of 0.01 to 0.80%, boron of 0.001 to 0.01% and cobalt of 1.0 to 5.0%, and a remaining part is mostly iron. Its structure is composed of a tempered martensite matrix.

Abstract: A heat-resistant nickel-based alloy having excellent welding properties, said nickel-based alloy consisting essentially of, in terms of wt. %, 0.05 to 0.25% of C, 18 to 25% of Cr, 15 to 25% of Co, at least one selected from the group consisting of up to 3.5% of Mo and 5 to 10% of W, with W+1/2Mo being 5 to 10%, 1.0 to 5.0% of Ti, 1.0 to 4.0% of Al, 0.5 to 4.5% of Ta, 0.2 to 3.0% of Nb, 0.005 to 0.10% of Zr, 0.001 to 0.01% of B and the balance being Ni and unavoidable impurities, wherein the (Al+Ti) content and the (W+1/2Mo) content are within the range surrounded by the lines connecting points A (Al+Ti: 5%, W+1/2Mo: 10%), B (Al+Ti: 5%, W+1/2Mo: 5%), C (Al+Ti: 7%, W+1/2Mo: 5%), and D (Al+Ti: 7%, W+1/2Mo: 10%) excluding the line A-B in FIG. 1.

Abstract: This invention relates to a high-strength and high-toughness heat-resisting steel formed from a heat-resisting steel containing, on a weight percentage basis, 0.08 to 0.25% carbon, up to 0.10% silicon, up to 0.10% manganese, 0.05 to 1.0% nickel, 10.0 to 12.5% chromium, 0.6 to 1.9% molybdenum, 1.0 to 1.95% tungsten, 0.10 to 0.35% vanadium, 0.02 to 0.10% niobium, 0.01 to 0.08% nitrogen, 0.001 to 0.01% boron, and 2.0 to 8.0% cobalt, the balance being substantially iron, and having a structure consisting of a tempered martensite matrix.

Abstract: There are provided high-strength and high-toughness heat-resistant cast steels applicable to steam turbine casings, precision cast vanes and valves. There is disclosed a high-strength and high-toughness heat-resistant cast steel formed of a heat-resistant cast steel consisting of, based on weight percentage: 0.08 to 0.25% of carbon; more than 0.1 not more than 0.5% of silicon; 1% or less of manganese; 0.05 to 1% of nickel; 9 to 12% of chromium; 0.3 to 1.5% of molybdenum; 1 to 1.95% of tungsten; 0.1 to 0.35% of vanadium; 0.02 to 0.1% of niobium; 0.01 to 0.08% of nitrogen; 0.001 to 0.01% of boron; and 2 to 8% of cobalt; the balance substantially being iron; and having a martensite matrix structure.

Abstract: A rotating blade or stationary vane of a gas turbine which is made of a nickel alloy containing Cr, Co, Mo, W, Ta, Al, Ti, C, B, Zr, and one or both of Mg and Ca. Additionally, the alloy may contain Hf, Pt, Rh and Re.

Abstract: The improved nickel-base heat-resistant alloy consists of 13.1-15.0% Cr (all percentages that follows are by weight), 8.5-10.5% Co, 1.0-3.5% Mo, 3.5-4.5% W, 3.0-5.5% Ta, 3.5-4.5% Al, 2.2-3.2% Ti, 0.06-0.12% C, 0.005-0.025% B, 0.010-0.05% Zr and 1-100 ppm of Mg and/or Ca, in the optional presence of 0-1.5% Hf and/or 0-0.5% of at least one element of Pt, Rh and Re, with the remainder being Ni and incidental impurities. The alloy has high strength and high resistance to oxidation and corrosion at elevated temperatures and, hence, is suitable for use as a constituent material for machine parts that are to be exposed to elevated temperatures.

Abstract: A heat resistant nickel base alloy which is excellent in not only hot and cold workability but also high temperature strength properties and which also possesses satisfactory oxidation resistance. The nickel base alloy consists essentially of 0.001-0.15 percent carbon, 0.0005-0.05 percent calcium, 20.0-126.0 percent chromium, 4.7-9.4 percent cobalt, 5.0-16.0 percent molybdenum, 0.5-4.0 percent tungsten, with the total of molybdenum plus tungsten being from 9.0 to 16.5 percent, and the balance nickel and inevitable impurities. The alloy may further contain one selected from the group consisting of (1) 0.3-1.5 percent aluminum and 0.1-1.0 percent titanium, (2) 0.001-0.30 percent at least one of yttrium and rare earth elements, and (3) 0.01-1.0 percent at least one of niobium, vanadium and tantalum, whereby the aforementioned characteristics are further enhanced.