Mitsubishi Heavy Industries Limited

Mitsubishi Jukogyo Kabushiki Kaisha

Mitsubishi Materials Corporation

Mitsubishi Steel Mfg. Co., Ltd.

Other

Kabushiki Kaisha Kobe Seiko Sho

Daido Tokushuko Kabushiki Kaisha

Mitsubishi Kinzoku Kabushiki Kaisha

Hisataka Kawai

Koji Takahashi

Ikuo Okada

Yoshikuni Kadoya

Taiji Torigoe

Ichiro Tsuji

Kensho Sahira

Akira Mitsuhashi

Ryotarou Magoshi

Ryotaro Magoshi

Kouji Takahashi

Itaru Tamura

Toshiharu Noda

Michio Okabe

Katsuhiko Abe

Ryuichi Yamamoto

Susumu Isobe

Saburou Wakita

Hiroshi Susukida

Toshiki Takeiri

Michi Misumi

Tsuyoki Kokubun

Toshio Kojima

Hitomi Itoh

Tomohiro Tsuchiyama

Makoto Yuge

Yasuhiko Yasumoto

Yukiko Nishiura

Ichirou Tsuji

Toshio Sakon

Shyuichi Sakashita

Shuichi Sakashita

Yoshinao Hibaru

Toshio Mochizuki

Takashi Kawabata

Takayuki Imazu

Kazunori Tokoro

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+&#xbd;(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.

Low thermal expansion Ni-base superalloy

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 Cr C is finely dispersed in matrix MCrAlY, where weight ratio of MCrAlY/Cr C is 1/1 to 3/1, is formed on base material (1) as sprayed coating and then diffusion heat treatment is added.

High temperature equipment

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.

High temperature corrosion-resistant and abrasion-resistant coating member, and manufacturing method thereof

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.

Columnar crystalline Ni-base heat-resistant alloy having high resistance to intergranular corrosion at high temperature, method of producing the alloy, large-size article, and method of producing large-size article from the alloy

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&deg; 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&deg; 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&deg; C. for 22 to 26 hours.

Property recovering method for Ni-base heat resistant alloy

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. Specifically, it relates to a process for the heat treatment of a Ni-base heat-resisting alloy having a specific composition which comprises the steps of subjecting the alloy to a first-stage solution treatment by keeping it at a specific temperature for a specific period of time; cooling the alloy to a second-stage solution treatment temperature at a specific cooling rate; subjecting the alloy to a second-stage solution treatment by keeping it at a specific temperature for a specific period of time; cooling the alloy rapidly to room temperature at a specific cooling rate; subjecting the alloy to a stabilizing treatment by keeping it at a specific temperature for a specific period of time; cooling the alloy rapidly to room temperature at a specific cooling rate; and subjecting the alloy to an aging treatment by keeping it at a specific temperature for a specific period of time.

Process for the heat treatment of a Ni-base heat-resisting alloy

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.

Material for gas turbine disk

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.

Highly tenacious ferritic heat resisting steel

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. Another alloy has substantially the same composition as described above except that the Cr content is 10 to 20% and the (Al+Ti) content and the (W+1/2Mo) content are within the range surrounded by the lines connecting points A, B, E (Al+Ti: 4%, W+1/2Mo: 5%), F (Al+Ti: 4%, W+1/2Mo: 0.5%), G (Al+Ti: 7%, W+1/2Mo: 0.5%) and D, excluding the line A-B-E, in FIG. 1.

Heat-resistant nickel-based alloy excellent in weldability

High-strength and high-toughness heat-resisting steel

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.

High-strength and high-toughness heat-resistant cast steel

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.

Rotating blade or stationary vane of a gas turbine

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.

Nickel-base heat-resistant alloys

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.

Heat resistant nickel base alloy excellent in workability and high

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Takasago, Japan

Hisataka Kawai