EP2233594A1 - Alliage à base de nickel pour rotor de turbine d'un système de turbine à vapeur et rotor de turbine de turbine à vapeur l'utilisant - Google Patents

Alliage à base de nickel pour rotor de turbine d'un système de turbine à vapeur et rotor de turbine de turbine à vapeur l'utilisant Download PDF

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Publication number
EP2233594A1
EP2233594A1 EP10002795A EP10002795A EP2233594A1 EP 2233594 A1 EP2233594 A1 EP 2233594A1 EP 10002795 A EP10002795 A EP 10002795A EP 10002795 A EP10002795 A EP 10002795A EP 2233594 A1 EP2233594 A1 EP 2233594A1
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Prior art keywords
turbine rotor
steam turbine
nickel
turbine
alloy
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EP10002795A
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German (de)
English (en)
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EP2233594B1 (fr
Inventor
Shigekazu Miyashita
Kiyoshi Imai
Masayuki Yamada
Kuniyoshi Nemoto
Takeo Suga
Takeo Takahashi
Kazutaka Ikeda
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Toshiba Corp
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Toshiba Corp
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    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
    • C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
    • C22F1/10—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of nickel or cobalt or alloys based thereon
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C1/00—Making non-ferrous alloys
    • C22C1/02—Making non-ferrous alloys by melting
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C1/00—Making non-ferrous alloys
    • C22C1/02—Making non-ferrous alloys by melting
    • C22C1/023—Alloys based on nickel
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C19/00—Alloys based on nickel or cobalt
    • C22C19/03—Alloys based on nickel or cobalt based on nickel
    • C22C19/05—Alloys based on nickel or cobalt based on nickel with chromium
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C19/00—Alloys based on nickel or cobalt
    • C22C19/03—Alloys based on nickel or cobalt based on nickel
    • C22C19/05—Alloys based on nickel or cobalt based on nickel with chromium
    • C22C19/051—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W
    • C22C19/055—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being at least 20% but less than 30%
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C19/00—Alloys based on nickel or cobalt
    • C22C19/03—Alloys based on nickel or cobalt based on nickel
    • C22C19/05—Alloys based on nickel or cobalt based on nickel with chromium
    • C22C19/051—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W
    • C22C19/056—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being at least 10% but less than 20%
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/31—Application in turbines in steam turbines

Definitions

  • the present invention relates to a nickel-base alloy for a turbine rotor of a steam turbine, and a turbine rotor of a steam turbine using this nickel-base alloy.
  • the turbine rotor of the steam turbine is required to endure high temperature and high stress, and as a material forming the turbine rotor, there is demanded an alloy having high strength, ductility, and toughness in a region ranging from room temperature to high temperature.
  • Ni-base alloys have insufficient high temperature strength, and therefore use of nickel (Ni)-base alloys is considered (see, for example, JP-A 7-150277 (KOKAI)). Due to its excellent high temperature strength and corrosion resistance, the Ni-base alloys have been widely used mainly as materials for jet engines and gas turbines. Typical examples include Inconel 617 alloy (manufactured by Special Metals Corporation) and Inconel 706 alloy (manufactured by Special Metals Corporation).
  • Ni-base alloy As a mechanism to enhance the high temperature strength of a Ni-base alloy, there is known one in which a precipitation phase called a gamma prime phase (Ni 3 (Al, Ti)) or a gamma double prime phase (Ni 3 Nb) is precipitated or both the phases are precipitated in the matrix of the Ni-base alloy by adding Al and Ti, to thereby ensure the high temperature strength.
  • a precipitation phase called a gamma prime phase (Ni 3 (Al, Ti)
  • Ni 3 Nb gamma double prime phase
  • the Inconel 706 alloy is one such example.
  • Ni-base alloys in which Co, Mo are added to strengthen (solid solution strengthening) a matrix of the Ni base to ensure high temperature strength, such as Inconel 617 alloy.
  • Ni-base alloys having higher high temperature strength than that of iron-base materials, and there is demanded improvement in composition to satisfy high temperature strength, forgeability, and the like, while maintaining hot workability of the Ni-base alloys.
  • An object of the present invention is to provide a Ni-base alloy for a turbine rotor of a steam turbine that is excellent in both high temperature strength and forgeability while maintaining the hot workability, and provide a turbine rotor of a steam turbine using the same.
  • An aspect of a nickel-base alloy for a turbine rotor of a steam turbine according to the present invention contains, in mass%,C: 0.01% to 0.15%, Cr: 18% to 28%, Co: 10% to 15%, Mo: 8% to 12%, Al: 0.5% to less than 1.5%, Ti: 0.7% to 3.0%, and B: 0.001% to 0.006%, the balance being nickel (Ni) and unavoidable impurities.
  • An aspect of a turbine rotor of a steam turbine according to the present invention is a turbine rotor provided to penetrate through a steam turbine to which high-temperature steam is introduced, in which at least a predetermined portion is constituted of the above-described nickel-base alloy for a turbine rotor of a steam turbine.
  • FIG. 1 is a constitution picture of a Ni-base alloy according to an embodiment of the present invention.
  • FIG. 2 is a graph showing results of a Greeble test.
  • FIG. 3 is a constitution picture of a Ni-base alloy.
  • FIG. 4 is a constitution picture of an Inconel 617 alloy.
  • Ni nickel-base alloy for a turbine rotor of a steam turbine according to the present invention and a turbine rotor of a steam turbine formed from this alloy will be described.
  • Ni-base alloys such as Inconel 706 alloy and Inconel 617 alloy are quite useful as turbine rotor materials. However, for further increase in efficiency of steam turbine power generating equipment, the Ni-base alloys are required to have satisfactory high temperature strength (mechanical strength at high temperature) and forgeability while maintaining hot workability (drawing or the like).
  • Inconel 617 alloy is an alloy with high temperature strength improved by solid solution strengthening of matrix of a Ni base by adding cobalt (Co) and molybdenum (Mo).
  • Co cobalt
  • Mo molybdenum
  • the Ni-base alloy for a turbine rotor of this embodiment is further strengthened using precipitation strengthening besides the solid solution strengthening.
  • Ni-base alloy for a turbine rotor of a stream turbine of this embodiment is based on the composition of Inconel 617 as a representative Ni-base alloy, and is improved in strength characteristics at high temperature and forgeability by performing addition and adjustment.
  • Ti content in the conventional Inconel 617 alloy is approximately 0.6% by mass, and the precipitation strengthening cannot be expected with this degree of content. Accordingly, the Ti content is increased to 0.7% to 3.0% by mass, so as to increase the amount of ⁇ ' phase (gamma prime phase (Ni 3 (Al, Ti))) to be precipitated.
  • ⁇ ' phase gamma prime phase (Ni 3 (Al, Ti)
  • FIG. 3 A constitution picture of a Ni-base alloy is shown in which Al concentration is increased to 1.6% by mass or higher and Ti concentration is increased to 0.7% by mass or higher so as to further improve the high temperature strength.
  • precipitation of a damaging phase called a ⁇ phase is recognized as shown by an arrow.
  • Ni-1.8Al-1.3Ti-23Cr-12Co-9Mo-0.1Ta-0.3Nb the number attached to the head of each constituent denotes the content (% by mass) of this constituent, and the balance being Ni.
  • the Al concentration is adjusted in the range of 0.5% to less than 1.5% by mass and tantalum (Ti) and niobium (Nb) are added as necessary, so as to allow stable precipitation of the ⁇ ' phase and improve stability of the ⁇ ' phase itself. Consequently, further strengthening of this Ni-base alloy is achieved.
  • Ni-base alloy for a turbine rotor of a steam turbine of this embodiment can be implemented as follows.
  • Ni-base alloys for a turbine rotor of a steam turbine namely, the above-described (alloy 1) to (alloy 5)
  • C is useful as a constitutional element of M 23 C 6 type carbide as a strengthened phase, and one of factors of maintaining creep strength of an alloy is to cause the M 23 C 6 type carbide to precipitate while the turbine is operating, particularly under a high-temperature environment at 650°C or higher. Further, it also has an effect to secure fluidity of molten metal during casting. When the content of C is less than 0.01% a sufficient precipitation amount of the carbide cannot be secured. Thus, the high temperature strength decreases, and the fluidity of molten metal during casting decreases significantly.
  • the content of C is over 0.15%, a constituent segregation trend increases when producing a large ingot, generation of M 6 C type carbide as an embrittlement phase is facilitated, and further the high temperature strength improves, but forgeability decreases.
  • the content of C is limited in the range of 0.01% to 0.15%.
  • Cr is an essential element to enhance oxidation resistance, corrosion resistance and high temperature strength of the Ni-base alloys. Moreover, it is essential as a constitutional element of the M 23 C 6 type carbide, and creep strength of the alloy is maintained by allowing the M 23 C 6 type carbide to precipitate while the turbine is operating, particularly under a high-tempeiature environment at 650°C or higher. Further, Cr can increase oxidation resistance under a high-temperature steam environment. When the content of Cr is less than 18%, the oxidation resistance decreases. On the other hand, when the content of Cr is over 28%, a trend to be coarse is enhanced by significantly facilitating the precipitation of the M 23 C 6 type carbide. Thus, the content of Cr is limited in the range of 18% to 28%.
  • Co has an effect to strengthen a parent phase in the Ni-base alloys by solid-solving into the parent phase.
  • the content of Co is less than 10%, the high temperature strength decreases.
  • the content of Co is over 15%, a weakening intermetallic compound phase is generated, and moreover forgeability decreases.
  • the content of Co is limited in the range of 10% to 15%.
  • Mo has an effect to enhance the strength of the matrix by solute effect. Further, Mo partially replaces the M 23 C 6 type carbide, and thereby stability of the carbide can be improved.
  • the content of Mo is less than 8%, the above-described effect is not exhibited, and when the content of Mo is over 12%, the component segregation trend when producing a large ingot increases and generation of M 6 C type carbide as an embrittlement phase is facilitated.
  • the content of Mo is limited in the range of 8% to 12%.
  • Al generates a ⁇ ' phase together with Ni and thereby can improve strength of the Ni-base alloys by precipitation.
  • the content of Al is less than 0.5%, the high temperature strength decreases.
  • the content of Al is 1.5% or more, it may facilitate precipitation of an embrittlement phase which is referred to as a ⁇ phase, along with decrease in forgeability.
  • the content of Al is limited in the range of 0.5% to less than 1.5%.
  • Ti generates the ⁇ ' phase together with Ni similarly to Al, and hence can strengthen the Ni-base alloys.
  • the content of Ti is less than 0.7%, the high temperature strength is equal to that of the conventional material.
  • the content of Ti is over 3%, hot workability decreases, possibly resulting in decrease of forgeability and increase of notch sensitivity.
  • the content of Ti is limited in the range of 0.7% to 3.0%.
  • B is segregated in a grain boundary to improve high-temperature properties. This effect can be exhibited when the content of B is 0.001% or more. However, when the content of B is over 0.006%, it may lead to grain boundary embrittlement. Thus, the content of B is limited in the range of 0.001% to 0.006%.
  • Ta has an effect to stabilize a precipitation strengthened phase by solid-solving in the ⁇ ' phase.
  • the content of Ta is less than 0.1%, the stabilization effect is not exhibited.
  • the content of Ta is over 0.7%, the high temperature strength improves but forgeability decreases.
  • the content of Ta is limited in the range of 0.1% to 0.7%.
  • Nb has an effect to enhance the high temperature strength and stabilize the ⁇ ' phase by solid-solving similarly to Ta.
  • the content of Nb is less than 0.1%, the above-described effect is not occred, and when the content of Nb is over 0.4%, the high temperature strength improves but forgeability decreases.
  • the content of Nb is limited in the range of 0.1% to 0.4%.
  • the above-described Ta and Nb such that the content of (Ta+2Nb) is in the range of 0.1% to 0.7%, they are solid-solved in the ⁇ ' phase to enhance the high temperature strength and stabilize the ⁇ ' phase precipitation.
  • Ta and Nb are each contained by at least 0.01% or more.
  • Si, Mn, Fe, Cu, and S are classified as unavoidable impurities in the Ni-base alloys for a turbine rotor of a steam turbine of this embodiment. It is desired that the remaining contents of these unavoidable impurities are made close to 0(zero)% as much as possible. Further, among these unavoidable impurities, it is preferred that at least Si and Mn are each suppressed to 0.1% or less. In the case of ordinary steel, Mn prevents brittleness by turning S (sulfur) contributing to brittleness to MnS. However, the content of S in the Ni-base alloys is quite small, and it is not necessary to add Mn.
  • the content of Mn is 0.1% or less and the remaining content thereof is close to 0(zero)% as much as possible.
  • Si is added to complement corrosion resistance in the case of ordinary steel.
  • the content of Cr is large and the corrosion resistance can be ensured sufficiently.
  • the content of Si is 0.1% or less and the remaining content thereof is close to 0(zero)% as much as possible.
  • FIG. 4 shoes microstructure of a conventional Inconel 617 alloy.
  • FIG. 1 [composition: Ni-0.05C-1.15Al-1.8Ti-23Cr-12Co-9Mo-0.1Ta-0.3Nb-0.003B] shoes microstructure of one of the Ni-base alloys for a turbine rotor of a steam turbine of this embodiment.
  • FIG. 1 in the Ni-base alloy for a turbine rotor of a steam turbine of this embodiment, it is possible to allow stable precipitation of fine ⁇ ' in the ⁇ matrix as shown by an arrow while suppressing the precipitation of the ⁇ phase, by the above-described alloy composition ranges.
  • Ni-base alloys for a turbine rotor of a steam turbine of this embodiment will be described.
  • An alloy whose constituents are adjusted as described above is melted and casted in the usual manner. Thereafter, this ingot is subjected to a stabilization treatment, ordinary hot forging, and a solution treatment.
  • a stabilization treatment In the solution treatment after the forging, it is desired that the temperature is not lower than the melting temperature of the ⁇ ' phase and not higher than the local melting starting temperature thereof.
  • the stabilization processing can be performed by heating for 3 to 72 hours in a temperature range of 1000°C to 1250°C, for example.
  • the solution treatment can be performed by heating for 3 to 24 hours in a temperature range of 1000°C to 1200°C and by quenching thereafter, for example. These treatments may be one that is performed in multiple stages. Moreover, as necessary, early precipitation of the ⁇ ' phase can be achieved by performing an aging treatment for 3 to 24 hours in a temperature range of 700°C to 800°C.
  • the 26 types of forged materials are each obtained by cutting off the portion of a surface as forged from the surface of a columnar ingot having a diameter of approximately 125 mm and a length of approximately 210 mm.
  • the forged materials after removing the surface scale as forged each had a diameter of 120 mm and a length of 200 mm.
  • These forged materials were subjected to a stabilization treatment for six hours at 1180°C, and immediately thereafter to hot forging. The hot forging was performed until the forging ratio becomes three. In this forging, the temperatures of the forged materials were measured, so as to pause the forging work once for performing reheating at 1180°C when the temperature of the forged materials decrease to 1000°C.
  • each forged article was subjected to a solution treatment in which it is heated for four hours at 1170°C and thereafter quenched.
  • an aging treatment for ten hours at 750°C was performed.
  • a test piece was sampled appropriately from each forged article after the aging treatment, and was subjected to various types of tests. Results of a tensile strength test (0.2% proof stress) from room temperature (23°C) to high temperature (700°C and 800°C) and forging status are shown in Table 2 for comparative examples 1 to 21 and examples 1 to 5 after the solution treatment and the aging treatment.
  • the tensile test was performed complying JIS Z 2241 (Method of tensile test for metallic materials).
  • the 700°C and 800°C as temperature conditions in the tensile test are set in view of temperature conditions of a steam turbine in normal operation and temperatures in which safety factors are counted.
  • the "forging ratio” shows values of "L 1 /L 0 " where L 0 and L 1 are lengths before and after forging.
  • the "number of reheating” is the number of times of reheating an object being forged until the "forging ratio" becomes three in a forging treatment.
  • the "forging crack” shows results of visual observation for the presence of any "forging crack” after forging, in which "none” indicates one with no “forging crack” and “present” indicates one with a forging crack.
  • the “forgeability” shows results of evaluating forgeability, in which "O” indicates one determined to have good forgeability, and "X” indicates one determined to have poor forgeability.
  • the examples 1 to 5 have high 0.2% proof stresses at respective temperatures, and hence are proved to have excellent forgeability. It is found that the examples have both improved high temperature strength and forgeability due to precipitation/solid solution strengthening as compared to the comparative examples.
  • Table 3 shows results of a Greeble test to evaluate hot workability of the comparative example 1 (equivalent to the conventional material Inconel 617) shown in Table 1 and the examples 1 to 5.
  • the Greeble test was performed at 900°C, 1000°C, 1100°C, 1200°C, and 1300°C at strain rate of 10% distortion/sec.
  • FIG. 2 is a graph showing Greeble test results of each sample shown in Table 3.
  • the horizontal axis of FIG. 2 shows test temperature (°C).
  • Reduction of area (drawing) shown on the vertical axis means a ratio of a cross-sectional area of a test piece after the test (after fractured) decreased from the cross-sectional area of the test piece before the test, to the cross-sectional area of the test piece before the test. In short, when this value is large, it means that the test piece has excellent hot workability.
  • the examples 1 to 5 are equivalent to the conventional material, and in which a drawing value of 50% or more is secured at 900°C to 1300°C that is a temperature range of forging. Thus it is found that there is no problem in manufacturing.
  • the Ni-base alloys for a turbine rotor of a steam turbine of this embodiment make it possible that, by composing in the constituent ranges of the above-described compositions, both the high temperature strength and the forgeability can be improved while maintaining the hot workability of conventional Ni-base alloys. Accordingly, the Ni-base alloys for a turbine rotor of a steam turbine of this embodiment can attain high reliability under a high-temperature environment as a turbine rotor material for a steam turbine to which high-temperature steam is introduced.
  • a turbine rotor provided to penetrate through a steam turbine to which high-temperature steam is introduced can be formed from one of the Ni-base alloys for a turbine rotor of a steam turbine of this embodiment.
  • the whole of the turbine rotor of a steam turbine may be formed from this Ni-base alloy, or particularly a part of the turbine rotor of the turbine that is subjected to high temperature may be formed from this Ni-base alloy.
  • the part of the turbine rotor of the steam turbine that is subjected to high temperature may be, specifically, the entire area of a high-pressure steam turbine unit, or an area from a high-pressure steam turbine unit to a part of an intermediate-pressure steam turbine unit, and the like.

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Crystallography & Structural Chemistry (AREA)
  • General Engineering & Computer Science (AREA)
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EP10002795.2A 2009-03-18 2010-03-17 Legierung auf Nickelbasis für den Turbinenrotor eines Dampfturbinensystems und Turbinenrotor einer Dampfturbine damit Active EP2233594B1 (fr)

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Application Number Priority Date Filing Date Title
JP2009066517A JP5127749B2 (ja) 2009-03-18 2009-03-18 蒸気タービンのタービンロータ用Ｎｉ基合金およびそれを用いた蒸気タービンのタービンロータ

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EP2233594A1 true EP2233594A1 (fr) 2010-09-29
EP2233594B1 EP2233594B1 (fr) 2015-06-17

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US (1) US20100239425A1 (fr)
EP (1) EP2233594B1 (fr)
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CN (1) CN101838757A (fr)

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EP2407565A1 (fr) * 2010-07-12 2012-01-18 Rolls-Royce plc Procédé pour améliorer les propriétés mécaniques d'un composant
EP2835434A3 (fr) * 2013-08-07 2015-05-27 Kabushiki Kaisha Toshiba Alliage à base de Ni pour le forgeage, son procédé de fabrication et composant de turbine

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JP2012207594A (ja) * 2011-03-30 2012-10-25 Mitsubishi Heavy Ind Ltd 回転機械のロータ及び回転機械
CN102162049B (zh) * 2011-04-07 2012-12-19 上海大学 一种超超临界汽轮机用镍基合金材料及其制备方法
JP2012255424A (ja) * 2011-06-10 2012-12-27 Toshiba Corp 蒸気タービンの鋳造用Ｎｉ基合金および蒸気タービンの鋳造部品
JP5703177B2 (ja) * 2011-09-12 2015-04-15 株式会社東芝 溶接用Ｎｉ基合金および溶加材
US20130209262A1 (en) * 2012-02-09 2013-08-15 Daniel Edward Matejczyk Method of manufacturing an airfoil
JP5921401B2 (ja) * 2012-02-10 2016-05-24 株式会社東芝 Ｎｉ基合金、その製造方法およびタービン用部品
JP5981251B2 (ja) * 2012-07-20 2016-08-31 株式会社東芝 鍛造用Ｎｉ基合金および鍛造部品
EP3083138A4 (fr) * 2013-12-17 2017-09-06 United Technologies Corporation Composants de turbine à gaz usinés par abrasion
US20170037737A1 (en) * 2015-08-05 2017-02-09 Rolls-Royce Corporation Rotating components with blind holes
CN105221190B (zh) * 2015-09-11 2018-06-05 杭州汽轮机股份有限公司 汽轮机用高温套筒及其制造方法
CN105112728B (zh) * 2015-09-29 2017-03-22 钢铁研究总院 一种700℃超超临界汽轮机转子用耐热合金及其制备方法
GB2561147B (en) * 2017-02-28 2021-09-08 Gkn Aerospace Sweden Ab A method for heat treatment of a nickel base alloy such as alloy 282, said alloy and components thereof
CN114799441B (zh) * 2022-04-15 2023-09-15 温州大学 一种含钴的Inconel625-Co合金及其制备方法

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EP2039789A1 (fr) * 2007-09-14 2009-03-25 Kabushiki Kaisha Toshiba Alliage à base de nickel pour rotor de turbine d'une turbine à vapeur et rotor de turbine d'une turbine à vapeur

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US20100239425A1 (en) 2010-09-23
JP5127749B2 (ja) 2013-01-23
CN101838757A (zh) 2010-09-22
EP2233594B1 (fr) 2015-06-17
JP2010215989A (ja) 2010-09-30

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