EP1715068B1 - Nickel-based super-heat-resistant alloy and gas turbine component using same - Google Patents
Nickel-based super-heat-resistant alloy and gas turbine component using same Download PDFInfo
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- EP1715068B1 EP1715068B1 EP04807451A EP04807451A EP1715068B1 EP 1715068 B1 EP1715068 B1 EP 1715068B1 EP 04807451 A EP04807451 A EP 04807451A EP 04807451 A EP04807451 A EP 04807451A EP 1715068 B1 EP1715068 B1 EP 1715068B1
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- corrosion
- gas turbine
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- 229910045601 alloy Inorganic materials 0.000 title abstract description 72
- 239000000956 alloy Substances 0.000 title abstract description 72
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 title abstract description 27
- 229910052759 nickel Inorganic materials 0.000 title abstract description 6
- 239000012535 impurity Substances 0.000 claims abstract description 13
- 238000000034 method Methods 0.000 claims abstract description 4
- 229910000601 superalloy Inorganic materials 0.000 claims description 33
- 229910052804 chromium Inorganic materials 0.000 claims description 17
- 229910052719 titanium Inorganic materials 0.000 claims description 17
- 229910052782 aluminium Inorganic materials 0.000 claims description 16
- 238000005266 casting Methods 0.000 claims description 15
- 229910052721 tungsten Inorganic materials 0.000 claims description 15
- 229910052799 carbon Inorganic materials 0.000 claims description 14
- 229910052796 boron Inorganic materials 0.000 claims description 13
- 229910052735 hafnium Inorganic materials 0.000 claims description 13
- 229910052750 molybdenum Inorganic materials 0.000 claims description 12
- 229910052715 tantalum Inorganic materials 0.000 claims description 12
- 229910052726 zirconium Inorganic materials 0.000 claims description 11
- 229910052758 niobium Inorganic materials 0.000 claims description 9
- 229910052702 rhenium Inorganic materials 0.000 claims description 8
- 238000007711 solidification Methods 0.000 claims description 7
- 230000008023 solidification Effects 0.000 claims description 7
- 230000007797 corrosion Effects 0.000 abstract description 44
- 238000005260 corrosion Methods 0.000 abstract description 44
- 230000003647 oxidation Effects 0.000 abstract description 27
- 238000007254 oxidation reaction Methods 0.000 abstract description 27
- 239000000463 material Substances 0.000 abstract description 10
- 239000000446 fuel Substances 0.000 abstract description 8
- 238000005242 forging Methods 0.000 abstract 1
- 239000010936 titanium Substances 0.000 description 23
- 239000011651 chromium Substances 0.000 description 21
- 230000000694 effects Effects 0.000 description 13
- 239000007789 gas Substances 0.000 description 13
- 239000000203 mixture Substances 0.000 description 12
- 239000010955 niobium Substances 0.000 description 10
- 239000013078 crystal Substances 0.000 description 7
- 238000010438 heat treatment Methods 0.000 description 6
- 238000001816 cooling Methods 0.000 description 5
- 230000008021 deposition Effects 0.000 description 5
- 239000006104 solid solution Substances 0.000 description 5
- 230000002787 reinforcement Effects 0.000 description 4
- 239000000243 solution Substances 0.000 description 4
- VYZAMTAEIAYCRO-UHFFFAOYSA-N Chromium Chemical compound [Cr] VYZAMTAEIAYCRO-UHFFFAOYSA-N 0.000 description 3
- 239000000567 combustion gas Substances 0.000 description 3
- 239000000295 fuel oil Substances 0.000 description 3
- XEEYBQQBJWHFJM-UHFFFAOYSA-N iron Substances [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 description 3
- 238000005486 sulfidation Methods 0.000 description 3
- ZOXJGFHDIHLPTG-UHFFFAOYSA-N Boron Chemical compound [B] ZOXJGFHDIHLPTG-UHFFFAOYSA-N 0.000 description 2
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 2
- ZOKXTWBITQBERF-UHFFFAOYSA-N Molybdenum Chemical compound [Mo] ZOKXTWBITQBERF-UHFFFAOYSA-N 0.000 description 2
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 2
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 2
- 239000010941 cobalt Substances 0.000 description 2
- 229910017052 cobalt Inorganic materials 0.000 description 2
- GUTLYIVDDKVIGB-UHFFFAOYSA-N cobalt atom Chemical compound [Co] GUTLYIVDDKVIGB-UHFFFAOYSA-N 0.000 description 2
- 230000005496 eutectics Effects 0.000 description 2
- VBJZVLUMGGDVMO-UHFFFAOYSA-N hafnium atom Chemical compound [Hf] VBJZVLUMGGDVMO-UHFFFAOYSA-N 0.000 description 2
- 229910052742 iron Inorganic materials 0.000 description 2
- 239000011733 molybdenum Substances 0.000 description 2
- GUCVJGMIXFAOAE-UHFFFAOYSA-N niobium atom Chemical compound [Nb] GUCVJGMIXFAOAE-UHFFFAOYSA-N 0.000 description 2
- WUAPFZMCVAUBPE-UHFFFAOYSA-N rhenium atom Chemical compound [Re] WUAPFZMCVAUBPE-UHFFFAOYSA-N 0.000 description 2
- GUVRBAGPIYLISA-UHFFFAOYSA-N tantalum atom Chemical compound [Ta] GUVRBAGPIYLISA-UHFFFAOYSA-N 0.000 description 2
- WFKWXMTUELFFGS-UHFFFAOYSA-N tungsten Chemical compound [W] WFKWXMTUELFFGS-UHFFFAOYSA-N 0.000 description 2
- 239000010937 tungsten Substances 0.000 description 2
- 229910017709 Ni Co Inorganic materials 0.000 description 1
- QCWXUUIWCKQGHC-UHFFFAOYSA-N Zirconium Chemical compound [Zr] QCWXUUIWCKQGHC-UHFFFAOYSA-N 0.000 description 1
- 229910001093 Zr alloy Inorganic materials 0.000 description 1
- 239000008186 active pharmaceutical agent Substances 0.000 description 1
- 230000032683 aging Effects 0.000 description 1
- 239000004411 aluminium Substances 0.000 description 1
- 238000005336 cracking Methods 0.000 description 1
- 238000002425 crystallisation Methods 0.000 description 1
- 230000008025 crystallization Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000002950 deficient Effects 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 239000004615 ingredient Substances 0.000 description 1
- 238000005495 investment casting Methods 0.000 description 1
- 239000003350 kerosene Substances 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 150000001247 metal acetylides Chemical class 0.000 description 1
- 239000003921 oil Substances 0.000 description 1
- 239000013535 sea water Substances 0.000 description 1
- 229910052720 vanadium Inorganic materials 0.000 description 1
- LEONUFNNVUYDNQ-UHFFFAOYSA-N vanadium atom Chemical compound [V] LEONUFNNVUYDNQ-UHFFFAOYSA-N 0.000 description 1
Images
Classifications
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- 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
- C22C19/057—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being less 10%
-
- 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%
Definitions
- the present invention relates to a Ni-base superalloy having an excellent resistance to corrosion at high temperatures, an excellent resistance to oxidation at high temperatures, and high-temperature strength, and gas turbine component using the same, in order to deal with low-quality fuel.
- Ni-base superalloy is widely used as industrial gas turbine components, for example, turbine blade materials such as Rene80 and IN792 having an excellent resistance to corrosion, Mar-M247 having an excellent resistance to oxidation and a high strength are known. Further, CMSX-11 having both a good resistance to corrosion and a high strength realized by single crystal casting of the high chromium content alloy is also known.
- Ni-base superalloys cannot share the properties of the high resistance to corrosion (Rene80, etc.) and the high resistance to oxidation and high strength (Mar-M247, etc.), so that there is a failure that they cannot be applied to improve the efficiency of a gas turbine dealing with low-quality fuel such as heavy oil.
- an alloy (CMSX-11, etc.) having a resistance to corrosion and a strength realized by single crystal casting of the high chromium content alloy does not have a sufficient resistance to oxidation, and moreover there is a problem with single-crystal material that the casting yield of components in complicated shapes is lowered.
- a high corrosion resistant and high strength alloy containing, by weight % (wt%), Cr: 6 to 12%, Al (aluminum): 4.5 to 6.5%, W(tungsten): 2 to 12%, Ta(tantalum): 2.5 to 10%, Mo(molybdenum) : up to 5.8%, Co (cobalt) : 0.1 to 3%, Nb(niobium) : 0.2 to 3%, Re (rhenium) : 0.1 to 4%, and Hf (hafnium) : up to 0.3%, having a P value (calculated by weight % by Formula (1) indicated below) of 2350 to 3280, and the balance of Ni and inevitable impurities is known.
- Ni series supper-alloy suitable for single-crystal solidification containing, by weight %, Co: 4.75 to 5.25%, Cr: 15.5 to 16.5%, Mo: 0.8 to 1.2%, W: 3.75 to 4.25%, Al: 3.75 to 4.25%, Ti: 1.75 to 2.25%, Ta: 4.75 to 5.25%, C: 0.006 to 0.04%, B: up to 0.01%, Zr: up to 0.01%, Hf: up to 1%, Nb: up to 1%, and Ni and impurity components added so as to reach 100% in total is known.
- this Ni series super-alloy contains Cr too much, so that the resistance to oxidation is insufficient.
- Ni-based single crystal supper-alloy containing, by weight %, Cr: 8 to 14%, Co: 3 to 7%, Al: 4 to 8%, Ti: up to 5%, W: 6 to 10%, Ta: 4 to 8%, Mo: 0.5 to 4%, Hf: up to 1.4%, Zr: up to 0.01%, C: up to 0.07%, B: up to 0.015%, and the balance of Ni and inevitable impurities, wherein 5% ⁇ Al + Ti, 4 ⁇ Al/Ti, and W + Ta + Mo ⁇ 18% is known.
- the Ni-based single crystal super-alloy is deficient in Ti due to the restriction of 4 ⁇ Al / Ti, so that the resistance to corrosion is insufficient.
- Ni-based super-alloy containing, by weight %, Cr: 7 to 12%, Co: 5 to 15%, Mo: 0.5 to 5%, W: 3 to 12%, Ta: 2 to 6%, Ti: 2 to 5%, Al: 3 to 5%, Nb: up to 2%, Hf: up to 2%, C: 0.03 to 0.25%, and B: 0.002 to 0.05% and composed of residual components of Ni and accompanying impurities is known.
- this Ni-based super-alloy is improved in the balance between the resistance to oxidation and the resistance to corrosion by an increase in the ratio of Al to Ti, the relation to the element added to increase the strength is not taken into account.
- Ni-based alloy containing, by weight %, Cr: 2 to 25%, Al: 1 to 7%, W: 2 to 15%, Ti: 0.5 to 5%, Nb: up to 3%, Mo: up to 6%, Ta: 1 to 12%, Re: up to 4%, Co: 7.5 to 25%, Fe (iron) : up to 0.5%, C: up to 0.2%, B: 0.002 to 0.035%, Hf: up to 2.0%, Zr: 0.02%, and Ni: 40% or more is known.
- this Ni-based alloy the relationship between the balance of elements and the material properties is not taken into account.
- Japanese Patent Publication No. 2843476 Japanese Patent Publication No. 3246376
- Japanese Patent Laid-Open Publication No. 2002-235135 Japanese Patent Laid-Open Publication No. 7-300639
- Japanese Patent Laid-Open Publication No. 5-59473 Japanese Patent Laid-Open Publication No. 9-170402 may be cited.
- WO 01/64964 A1 discloses a nickel base superalloy suitable for the production of a large, crack-free nickel-base superalloy gas turbine bucket suitable for use in a large land-based utility gas turbine engine, comprising, by weight percents: Chromium 7.0 to 12.0; Carbon 0.06 to 0.10; Cobalt 5.0 to 15; Titanium 3.0 to 5.0; Aluminium 3.0 to 5.0; Tungsten 3.0 to 12.0; Molybdenum 1.0 to 5.0; Boron 0.0080 to 0.01; Rhenium 0 to 10.0; Tantalum 2.0 to 6.0; Columbium 0 to 2.0; Vanadium 0 to 3.0; Hafnium 0 to 2.0; and remainder nickel and incidental impurities.
- the present invention is intended to provide, as a component material of an industrial gas turbine, a Ni-base superalloy having an excellent resistance to hot corrosion with low-quality fuel and an excellent resistance to oxidation at high temperatures and a high-temperature strength to improve the thermal efficiency, also having a high yield at the precision casting process, and gas turbine component using the same.
- the first Ni-base superalloy of the present invention consists of: by weight %, Co: 9 to 11%, Cr: 9 to 12%, Mo: up to 1%, W: 6 to 9%, Al: 4 to 5%, Ti: 4 to 5%, Nb: up to 1%, Ta: up to 3%, Hf: 0.5 to 2.5%, Re: up to 3%, C: 0.05 to 0.15%, B: 0.005 to 0.015%, Zr: up to 0.05%, and the balance of Ni and inevitable impurities. Further, the weight % of Hf is preferably 0.5 to 1%.
- the second Ni-base superalloy of the present invention consists of: by weight %, Co: 9 to 10%, Cr: 9 to 10%, Mo: 0.5 to 1%, W: 6 to 8%, Al: 4 to 5%, Ti: 4 to 5%, Ta: 2 to 3%, Hf: 0.5 to 2.5%, Re: 1 to 3%, C: 0.05 to 0.1%, B: 0.005 to 0.01%, Zr: up to 0.02%, and the balance of Ni and inevitable impurities. Further, the weight % of Hf is preferably 0.5 to 1%.
- the third Ni-base superalloy of the present invention consists of: by weight %, Co: 10 to 11%, Cr: 10 to 12%, W: 8 to 9%, Al: 4 to 5%, Ti: 4 to 5%, Nb: up to 1%, Hf: 0.5 to 2.5%, C: 0.05 to 0.15%, B: 0.005 to 0.015%, Zr: 0.01 to 0.05%, and the balance of Ni and inevitable impurities. Further, the weight % of Hf is preferably 0.5 to 1%.
- the gas turbine component of the present invention is manufactured by using any of the first to third Ni-base superalloys aforementioned and is preferably manufactured by using the directional solidification casting method.
- the present invention was developed, to realize the coexistence of the resistance to corrosion at high temperatures and the resistance to oxidation at high temperatures and high-temperature strength, by producing and evaluating many alloys by way of trial, as a result, adjusting the quantity ratio of Cr, Al, and Ti to an appropriate range, within the composition range, finding that W is effective as an element for contributing to strength improvement and little badly affecting the resistance to corrosion, and furthermore taking the phase stability judged from the solid solution quantity to the ⁇ (gamma) phase and ⁇ ' (gamma prime) phase into account.
- the quantity ratio of Cr contributing to the resistance to corrosion in a multiple environment of sulfidation and oxidation, Al for generating the ⁇ ' phase and contributing to the high-temperature strength and resistance to oxidation, and Ti for contributing to the resistance to corrosion is within an appropriate range, and the reinforced elements mainly W whose additional quantity is decided by contribution to strength improvement and influence on corrosion resistance are added to the concerned quantity ratio, thus the resistance to corrosion at high temperatures, the resistance to oxidation at high temperatures and high-temperature strength can be made excellent. Further, the Ni-base superalloys can obtain sufficiently high strength for practical use in the columnar grain material state, so that there is no need to set single crystallization as a precondition.
- the second Ni-base superalloy is suitable for columnar crystalline blades or single crystalline blades by directional solidification casting and can exhibit the properties of corrosion resistance, oxidation resistance, and strength on a high level
- the third Ni-base superalloy is suited for polycrystalline blades by conventional casting or columnar crystalline blades by directional solidification casting, and can suppress the material cost while maintaining the properties of corrosion resistance, oxidation resistance, and strength. Therefore, application of the present invention to turbine blades of an industrial gas turbine dealing with low-quality fuel is effective in improvement of the thermal efficiency and reliability of the gas turbine.
- gas turbine component of the present invention has better tolerance than the exclusive single crystal material for the reduction in strength due to casting defects such as low-angle grain boundaries or high-angle grain boundaries, and the allowable restriction range is wide, so that a high yield can be ensured at the casting process of gas turbine component in complicated shapes.
- Mo improves the high-temperature strength by solid solution reinforcement and deposition hardening, when the content thereof is more than 1 wt%, the resistance to corrosion is lowered. Further, the second alloy, when the content of Mo is less than 0.5 wt%, cannot obtain the aforementioned effect.
- W improves the high-temperature strength by solid solution reinforcement and deposition hardening, when the content thereof is less than 6 wt% (for the third alloy, 8 wt%), the effect cannot be obtained, and when it is more than 9 wt% (for the second alloy, 8 wt%), the TCP phase is generated and the high-temperature strength is lowered. Further, although W is generally considered to lower the resistance to corrosion, knowledge that in the composition area of the present invention, there is few effect by W on the resistance to corrosion is obtained.
- Al generates the ⁇ ' phase and improves the high-temperature strength and resistance to oxidation, when the content thereof is less than 4 wt%, the effect cannot be obtained, and when it is more than 5 wt%, the eutectic ⁇ ' phase is increased in amount, and the solution heat treatment becomes difficult to be performed, and the resistance to corrosion is lowered.
- Ti improves the resistance to corrosion, when the content thereof is less than 4 wt%, the effect cannot be obtained, and when it is more than 5 wt%, the resistance to oxidation is lowered, and the heat treatment property is lowered.
- Nb is fused in the ⁇ ' phase and improves the high-temperature strength, when the content thereof is more than 1 wt%, it is deposited in the grain boundaries, and lowers the high-temperature strength.
- Ta improves the high-temperature strength by solid solution reinforcement and deposition hardening, when the content thereof is more than 3 wt%, the eutectic ⁇ ' phase is increased in amount, and the solution heat treatment becomes difficult to be performed. Further, the second alloy, when the content of Ta is less than 2 wt%, cannot obtain the aforementioned effect.
- Hf reinforces the grain boundaries and improves the high-temperature strength and ductility and is effective to prevent intergranular cracking during DS casting, when the content thereof is less than 0.5 wt%, the effect cannot be obtained, and when it is more than 2.5 wt%, it segregates in the grain boundaries, and lowers the high-temperature strength.
- Re improves the high-temperature strength by solid solution reinforcement and particularly improves the resistance to corrosion at 900°C or higher, when the content thereof is more than 3 wt%, the ductility is deteriorated by deposition of the TCP phase, and the specific gravity is increased, and the cost is increased. Further, the second alloy cannot obtain the aforementioned effect when the content of Re is less than 1 wt%.
- B forms boronides and reinforces the grain boundaries, when the content thereof is less than 0.005 wt%, the effect cannot be obtained, and when it is more than 0.015 wt% (for the second alloy, 0.01 wt%), the ductility and toughness are lowered, and the high-temperature strength is lowered.
- Zr reinforces the grain boundaries, when the content thereof is more than 0.05 wt% (for the second alloy, 0.02 wt%), the ductility and toughness are lowered, and the high-temperature strength is lowered. Further, the third alloy cannot obtain the aforementioned effect when the content of Zr is less than 0.01 wt%.
- Ni-base superalloys (alloys 1 to 3 of the present invention and comparison alloys 1 to 3) having the component composition shown in Table 1 (the component compositions of the existing alloy 1 (Rene80H) and existing alloy 2 (Mar-M247) are also shown) are prepared, and these Ni-base superalloys are solidified under the condition of withdrawing speed 200 mm/h using a directional solidification casting furnace, and columnar crystalline castings are manufactured. Next, the heat treatment indicated below is performed, thus the respective Ni-base superalloys are obtained.
- test specimen shape Diameter of 10 mm, length of 100 mm
- Test conditions In combustion gas with corrosive ingredients (sulfuric oil, artificial seawater) added into kerosene fuel, at a combustion gas temperature of 1050°C, air cooling after exposure for 100 hours, repeated 5 times (500 hours in total)
- test specimen shape Diameter of 10 mm, length of 25 mm
- Test conditions In the atmosphere, at 950°C, air cooling after exposure for 500 hours
- test specimen shape Diameter of 4 mm, gauge length of 24 mm
- Test conditions In the atmosphere, at 900°C, at 392 MPa
- the alloy 1 of the present invention is excellent in the resistance to corrosion, resistance to oxidation, and strength and is particularly suited to use as a directional solidification material when higher strength is needed.
- the alloy 2 of the present invention is suited to use under the condition that the resistance to oxidation and strength are needed, and the resistance to corrosion is within the tolerance to use the heavy oil fuel.
- the alloy 3 of the present invention is suited to use under the condition that the resistance to corrosion is needed.
- the existing alloy 1 is widely used as a turbine blade material of a gas turbine and is excellent in the resistance to corrosion, as compared with the composition range of the alloys 1 to 3 of the present invention, it contains much Cr and little Al, so that the resistance to oxidation is low, thus the existing alloy 1 cannot deal with high-temperature demands of combustion gas aiming at improvement of thermal efficiency.
- the existing alloy 2 is excellent in the resistance to oxidation and strength, as compared with the composition range of the alloys 1 to 3 of the present invention, it contains little Cr and Ti and much Al, so that the resistance to corrosion is low, thus the existing alloy 2 cannot deal with heavy oil fuel.
- the comparison alloy 1 (almost corresponding to the composition range described in Japanese Patent Laid-Open Publication No. 5-59473 and Japanese Patent Laid-Open Publication No. 9-170402 ), as compared with the composition range of the alloys 1 to 3 of the present invention, contains little Ti, so that the resistance to corrosion is insufficient.
- the comparison alloy 2 (almost corresponding to the composition range described in Japanese Patent Laid-Open Publication No. 9-170402 ), as compared with the composition range of the alloys 1 to 3 of the present invention, contains much Cr and littleAl and W, so that the strength is insufficient.
- the comparison alloy 3 (almost corresponding to the composition range described in Japanese Patent Laid-Open Publication No. 5-59473 ), as compared with the composition range of the alloys 1 to 3 of the present invention, contains much Mo, so that the resistance to corrosion is insufficient.
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Abstract
Description
- The present invention relates to a Ni-base superalloy having an excellent resistance to corrosion at high temperatures, an excellent resistance to oxidation at high temperatures, and high-temperature strength, and gas turbine component using the same, in order to deal with low-quality fuel.
- The Ni-base superalloy is widely used as industrial gas turbine components, for example, turbine blade materials such as Rene80 and IN792 having an excellent resistance to corrosion, Mar-M247 having an excellent resistance to oxidation and a high strength are known.
Further, CMSX-11 having both a good resistance to corrosion and a high strength realized by single crystal casting of the high chromium content alloy is also known. - These existing Ni-base superalloys cannot share the properties of the high resistance to corrosion (Rene80, etc.) and the high resistance to oxidation and high strength (Mar-M247, etc.), so that there is a failure that they cannot be applied to improve the efficiency of a gas turbine dealing with low-quality fuel such as heavy oil.
Further, an alloy (CMSX-11, etc.) having a resistance to corrosion and a strength realized by single crystal casting of the high chromium content alloy does not have a sufficient resistance to oxidation, and moreover there is a problem with single-crystal material that the casting yield of components in complicated shapes is lowered. - To solve the problems of the existing Ni-base superalloys, a high corrosion resistant and high strength alloy containing, by weight % (wt%), Cr: 6 to 12%, Al (aluminum): 4.5 to 6.5%, W(tungsten): 2 to 12%, Ta(tantalum): 2.5 to 10%, Mo(molybdenum) : up to 5.8%, Co (cobalt) : 0.1 to 3%, Nb(niobium) : 0.2 to 3%, Re (rhenium) : 0.1 to 4%, and Hf (hafnium) : up to 0.3%, having a P value (calculated by weight % by Formula (1) indicated below) of 2350 to 3280, and the balance of Ni and inevitable impurities is known.
However, this high corrosion resistant and high strength alloy does not contain Titanium, so that the resistance to corrosion in a high-temperature corrosive environment where oxidation and sulfidation are superimposed is insufficient. - Further, a large casting of columnar grained Ni-base heat resistant alloy having an excellent high-temperature resistance to intergranular corrosion, containing, by weight %, Cr: 12.0 to 14.3%, Co: 8.5 to 11.0 %, Mo: 1. 0 to 3.5%, W: 3.5 to 6.2%, Ta: 3.0 to 5.5%, Al: 3.5 to 4.5%, Ti: 2. 0 to 3.2%, C(carbon): 0.04 to 0.12%, B(boron): 0.005 to 0.05%, and Zr(zirconium): 0.001 to 5 ppm and the balance of Ni and inevitable impurities is known.
However, in the large casting of columnar grained Ni-based heat resistant alloy, the quantity ratio of Cr, Al, and Ti is inappropriate, so that the resistance to corrosion and the resistance to oxidation cannot coexist with each other. - Furthermore, a Ni series supper-alloy suitable for single-crystal solidification containing, by weight %, Co: 4.75 to 5.25%, Cr: 15.5 to 16.5%, Mo: 0.8 to 1.2%, W: 3.75 to 4.25%, Al: 3.75 to 4.25%, Ti: 1.75 to 2.25%, Ta: 4.75 to 5.25%, C: 0.006 to 0.04%, B: up to 0.01%, Zr: up to 0.01%, Hf: up to 1%, Nb: up to 1%, and Ni and impurity components added so as to reach 100% in total is known.
However, this Ni series super-alloy contains Cr too much, so that the resistance to oxidation is insufficient. - Furthermore, a high corrosion resistance Ni-based single crystal supper-alloy containing, by weight %, Cr: 8 to 14%, Co: 3 to 7%, Al: 4 to 8%, Ti: up to 5%, W: 6 to 10%, Ta: 4 to 8%, Mo: 0.5 to 4%, Hf: up to 1.4%, Zr: up to 0.01%, C: up to 0.07%, B: up to 0.015%, and the balance of Ni and inevitable impurities, wherein 5% ≤ Al + Ti, 4 ≤ Al/Ti, and W + Ta + Mo ≤ 18% is known. However, the Ni-based single crystal super-alloy is deficient in Ti due to the restriction of 4 ≤ Al / Ti, so that the resistance to corrosion is insufficient.
- Further, a Ni-based super-alloy containing, by weight %, Cr: 7 to 12%, Co: 5 to 15%, Mo: 0.5 to 5%, W: 3 to 12%, Ta: 2 to 6%, Ti: 2 to 5%, Al: 3 to 5%, Nb: up to 2%, Hf: up to 2%, C: 0.03 to 0.25%, and B: 0.002 to 0.05% and composed of residual components of Ni and accompanying impurities is known.
Although it is said that this Ni-based super-alloy is improved in the balance between the resistance to oxidation and the resistance to corrosion by an increase in the ratio of Al to Ti, the relation to the element added to increase the strength is not taken into account. - Furthermore, a Ni-based alloy containing, by weight %, Cr: 2 to 25%, Al: 1 to 7%, W: 2 to 15%, Ti: 0.5 to 5%, Nb: up to 3%, Mo: up to 6%, Ta: 1 to 12%, Re: up to 4%, Co: 7.5 to 25%, Fe (iron) : up to 0.5%, C: up to 0.2%, B: 0.002 to 0.035%, Hf: up to 2.0%, Zr: 0.02%, and Ni: 40% or more is known.
However, in this Ni-based alloy, the relationship between the balance of elements and the material properties is not taken into account. - As documents concerning the background art, Japanese Patent Publication No.
2843476 3246376 2002-235135 7-300639 5-59473 9-170402
WO 01/64964 A1 Columbium 0 to 2.0;Vanadium 0 to 3.0; Hafnium 0 to 2.0; and remainder nickel and incidental impurities. - The present invention is intended to provide, as a component material of an industrial gas turbine, a Ni-base superalloy having an excellent resistance to hot corrosion with low-quality fuel and an excellent resistance to oxidation at high temperatures and a high-temperature strength to improve the thermal efficiency, also having a high yield at the precision casting process, and gas turbine component using the same.
- To solve the problem aforementioned, the first Ni-base superalloy of the present invention consists of: by weight %, Co: 9 to 11%, Cr: 9 to 12%, Mo: up to 1%, W: 6 to 9%, Al: 4 to 5%, Ti: 4 to 5%, Nb: up to 1%, Ta: up to 3%, Hf: 0.5 to 2.5%, Re: up to 3%, C: 0.05 to 0.15%, B: 0.005 to 0.015%, Zr: up to 0.05%, and the balance of Ni and inevitable impurities.
Further, the weight % of Hf is preferably 0.5 to 1%. - To solve the problem aforementioned, the second Ni-base superalloy of the present invention consists of: by weight %, Co: 9 to 10%, Cr: 9 to 10%, Mo: 0.5 to 1%, W: 6 to 8%, Al: 4 to 5%, Ti: 4 to 5%, Ta: 2 to 3%, Hf: 0.5 to 2.5%, Re: 1 to 3%, C: 0.05 to 0.1%, B: 0.005 to 0.01%, Zr: up to 0.02%, and the balance of Ni and inevitable impurities.
Further, the weight % of Hf is preferably 0.5 to 1%. - To solve the problem aforementioned, the third Ni-base superalloy of the present invention consists of: by weight %, Co: 10 to 11%, Cr: 10 to 12%, W: 8 to 9%, Al: 4 to 5%, Ti: 4 to 5%, Nb: up to 1%, Hf: 0.5 to 2.5%, C: 0.05 to 0.15%, B: 0.005 to 0.015%, Zr: 0.01 to 0.05%, and the balance of Ni and inevitable impurities.
Further, the weight % of Hf is preferably 0.5 to 1%. - To solve the problems aforementioned, the gas turbine component of the present invention is manufactured by using any of the first to third Ni-base superalloys aforementioned and is preferably manufactured by using the directional
solidification casting method. - The present invention was developed, to realize the coexistence of the resistance to corrosion at high temperatures and the resistance to oxidation at high temperatures and high-temperature strength, by producing and evaluating many alloys by way of trial, as a result, adjusting the quantity ratio of Cr, Al, and Ti to an appropriate range, within the composition range, finding that W is effective as an element for contributing to strength improvement and little badly affecting the resistance to corrosion, and furthermore taking the phase stability judged from the solid solution quantity to the γ (gamma) phase and γ' (gamma prime) phase into account.
- According to the Ni-base superalloys of the present invention, the quantity ratio of Cr contributing to the resistance to corrosion in a multiple environment of sulfidation and oxidation, Al for generating the γ' phase and contributing to the high-temperature strength and resistance to oxidation, and Ti for contributing to the resistance to corrosion is within an appropriate range, and the reinforced elements mainly W whose additional quantity is decided by contribution to strength improvement and influence on corrosion resistance are added to the concerned quantity ratio, thus the resistance to corrosion at high temperatures, the resistance to oxidation at high temperatures and high-temperature strength can be made excellent.
Further, the Ni-base superalloys can obtain sufficiently high strength for practical use in the columnar grain material state, so that there is no need to set single crystallization as a precondition.
Particularly, the second Ni-base superalloy is suitable for columnar crystalline blades or single crystalline blades by directional solidification casting and can exhibit the properties of corrosion resistance, oxidation resistance, and strength on a high level, and the third Ni-base superalloy is suited for polycrystalline blades by conventional casting or columnar crystalline blades by directional solidification casting, and can suppress the material cost while maintaining the properties of corrosion resistance, oxidation resistance, and strength.
Therefore, application of the present invention to turbine blades of an industrial gas turbine dealing with low-quality fuel is effective in improvement of the thermal efficiency and reliability of the gas turbine. - Further, the gas turbine component of the present invention has better tolerance than the exclusive single crystal material for the reduction in strength due to casting defects such as low-angle grain boundaries or high-angle grain boundaries, and the allowable restriction range is wide, so that a high yield can be ensured at the casting process of gas turbine component in complicated shapes.
-
-
Fig. 1 is an illustration showing the results of the hot corrosion test for the Ni-base superalloys of the present invention and existing Ni-base superalloys. -
Fig. 2 is an illustration showing the results of the high-temperature oxidation test for the Ni-base superalloys of the present invention and existing Ni-base superalloys. -
Fig. 3 is an illustration showing the results of the creep test for the Ni-base superalloys of the present invention and existing Ni-base superalloys. - Although Co expands the solution heat treatment temperature range, when the content thereof is less than 9 wt% (forthethirdalloy, 10wt%), the effect cannot be obtained, and when it is more than 11 wt% (for the second alloy, 10 wt%), the deposition of the γ' phase is reduced and the high-temperature strength is lowered.
- Although Cr particularly improves the resistance to corrosion in a multiple environment of sulfidation and oxidation, when the content thereof is less than 9 wt% (for the third alloy, 10 wt%), the effect cannot be obtained and when it is more than 12 wt% (for the second alloy, 10 wt%), a TCP (Topologically Close Packed) phase is generated and the high-temperature strength is lowered.
- Although Mo improves the high-temperature strength by solid solution reinforcement and deposition hardening, when the content thereof is more than 1 wt%, the resistance to corrosion is lowered.
Further, the second alloy, when the content of Mo is less than 0.5 wt%, cannot obtain the aforementioned effect. - AlthoughW improves the high-temperature strength by solid solution reinforcement and deposition hardening, when the content thereof is less than 6 wt% (for the third alloy, 8 wt%), the effect cannot be obtained, and when it is more than 9 wt% (for the second alloy, 8 wt%), the TCP phase is generated and the high-temperature strength is lowered.
Further, although W is generally considered to lower the resistance to corrosion, knowledge that in the composition area of the present invention, there is few effect by W on the resistance to corrosion is obtained. - Although Al generates the γ' phase and improves the high-temperature strength and resistance to oxidation, when the content thereof is less than 4 wt%, the effect cannot be obtained, and when it is more than 5 wt%, the eutectic γ' phase is increased in amount, and the solution heat treatment becomes difficult to be performed, and the resistance to corrosion is lowered.
- Although Ti improves the resistance to corrosion, when the content thereof is less than 4 wt%, the effect cannot be obtained, and when it is more than 5 wt%, the resistance to oxidation is lowered, and the heat treatment property is lowered.
- Although Nb is fused in the γ' phase and improves the high-temperature strength, when the content thereof is more than 1 wt%, it is deposited in the grain boundaries, and lowers the high-temperature strength.
- Although Ta improves the high-temperature strength by solid solution reinforcement and deposition hardening, when the content thereof is more than 3 wt%, the eutectic γ' phase is increased in amount, and the solution heat treatment becomes difficult to be performed.
Further, the second alloy, when the content of Ta is less than 2 wt%, cannot obtain the aforementioned effect. - Although Hf reinforces the grain boundaries and improves the high-temperature strength and ductility and is effective to prevent intergranular cracking during DS casting, when the content thereof is less than 0.5 wt%, the effect cannot be obtained, and when it is more than 2.5 wt%, it segregates in the grain boundaries, and lowers the high-temperature strength.
- Although Re improves the high-temperature strength by solid solution reinforcement and particularly improves the resistance to corrosion at 900°C or higher, when the content thereof is more than 3 wt%, the ductility is deteriorated by deposition of the TCP phase, and the specific gravity is increased, and the cost is increased.
Further, the second alloy cannot obtain the aforementioned effect when the content of Re is less than 1 wt%. - Although C forms carbides and reinforces the grain boundaries, when the content thereof is less than 0.05 wt%, the effect cannot be obtained, and when it is more than 0.15 wt% (for the second alloy, 0.1 wt%), an excessive carbide is generated, and the high-temperature strength is lowered.
- Although B forms boronides and reinforces the grain boundaries, when the content thereof is less than 0.005 wt%, the effect cannot be obtained, and when it is more than 0.015 wt% (for the second alloy, 0.01 wt%), the ductility and toughness are lowered, and the high-temperature strength is lowered.
- Although Zr reinforces the grain boundaries, when the content thereof is more than 0.05 wt% (for the second alloy, 0.02 wt%), the ductility and toughness are lowered, and the high-temperature strength is lowered.
Further, the third alloy cannot obtain the aforementioned effect when the content of Zr is less than 0.01 wt%. - Ni-base superalloys (
alloys 1 to 3 of the present invention andcomparison alloys 1 to 3) having the component composition shown in Table 1 (the component compositions of the existing alloy 1 (Rene80H) and existing alloy 2 (Mar-M247) are also shown) are prepared, and these Ni-base superalloys are solidified under the condition of withdrawingspeed 200 mm/h using a directional solidification casting furnace, and columnar crystalline castings are manufactured.
Next, the heat treatment indicated below is performed, thus the respective Ni-base superalloys are obtained. -
- Solution treatment: At 1200 to 1260°C, holding for 2 hours, then air cooling
- Aging: First stage, at 1080°C, holding for 4 hors, then air cooling
-
[Table 1] Ni Co Cr Mo W Al Ti Nb Ta Hf Re C B Zr Alloy 1 of present invention Remainder 10 10 0.8 7 4 4 0 2.5 0.5 2 0.1 0.01 0.01 Alloy 2 of present inventionRemainder 11 11 0 8.5 4 4.5 0 0 1 0 0.11 0.01 0.05 Alloy 3 ofpresent invention Remainder 10 12 0.5 6 4 4.5 0.5 0 1 0 0.1 0.01 0.01 Comparison alloy 1Remainder 12 8 0 5 6 2 0 4 1 2 0.07 0.015 0 Comparison alloy 2Remainder 9 14 2 4 3 5 0 2 0.7 0 0.16 0.015 0.06 Comparison alloy 3Remainder 9 10 3 4 3 . 5 5 0 2 0 . 7 0 0.16 0.015 0.06 Existing alloy 1Remainder 9.2 13.9 4.1 4.1 3.1 4.8 0 0 0.7 0 0.16 0.015 0.06 Existing alloy 1Remainder 10 8.3 0.7 10 5.5 1 0 3 1.5 0 0.15 0.015 0.05 (Unit: Weight %) - For the test specimens of the
alloys 1 to 3 of the present invention obtained and the existingalloys Fig. 1 .
Test specimen shape: Diameter of 10 mm, length of 100 mm
Test conditions: In combustion gas with corrosive ingredients (sulfuric oil, artificial seawater) added into kerosene fuel, at a combustion gas temperature of 1050°C, air cooling after exposure for 100 hours, repeated 5 times (500 hours in total) - Further, for the test specimens of the
alloys 1 to 3 of the present invention obtained and the existingalloys Fig. 2 .
Test specimen shape: Diameter of 10 mm, length of 25 mm
Test conditions: In the atmosphere, at 950°C, air cooling after exposure for 500 hours - Furthermore, for the test specimens of the
alloys 1 to 3 of the present invention obtained and the existingalloys Fig. 3 .
Test specimen shape: Diameter of 4 mm, gauge length of 24 mm
Test conditions: In the atmosphere, at 900°C, at 392 MPa - On the basis of the existing
alloy 1, the maximum corrosion depth ratio in the hot corrosion test, the mass change ratio in the oxidation test, and the rupture life ratio in the creep test for thealloys 1 to 3 of the present invention, thecomparison alloys 1 to 3, and the existingalloy 2 are checked and the results are shown in Table 2. -
[Table 2] Maximum corrosion depth ratio in hot corrosion test Mass change ratio in oxidation test Rupture life ratio in creep test Alloy 1 of present invention 0.73 0.28 3.19 Alloy 2 of present invention1.20 0.44 1.32 Alloy 3 of present invention0.67 0.57 0.81 Comparison alloy 14.73 0.08 2.82 Comparison alloy 20.85 0.83 0.30 Comparison alloy 31.69 0.60 0.95 Existing alloy 11.00 1.00 1.00 Existing alloy 22.20 0.09 3.12 - As shown in
Figs. 1 to 3 and Table 2, thealloy 1 of the present invention is excellent in the resistance to corrosion, resistance to oxidation, and strength and is particularly suited to use as a directional solidification material when higher strength is needed.
Thealloy 2 of the present invention is suited to use under the condition that the resistance to oxidation and strength are needed, and the resistance to corrosion is within the tolerance to use the heavy oil fuel.
Further, thealloy 3 of the present invention is suited to use under the condition that the resistance to corrosion is needed. - Although the existing
alloy 1 is widely used as a turbine blade material of a gas turbine and is excellent in the resistance to corrosion, as compared with the composition range of thealloys 1 to 3 of the present invention, it contains much Cr and little Al, so that the resistance to oxidation is low, thus the existingalloy 1 cannot deal with high-temperature demands of combustion gas aiming at improvement of thermal efficiency.
Further, although the existingalloy 2 is excellent in the resistance to oxidation and strength, as compared with the composition range of thealloys 1 to 3 of the present invention, it contains little Cr and Ti and much Al, so that the resistance to corrosion is low, thus the existingalloy 2 cannot deal with heavy oil fuel. - The comparison alloy 1 (almost corresponding to the composition range described in Japanese Patent Laid-Open Publication No.
5-59473 9-170402 alloys 1 to 3 of the present invention, contains little Ti, so that the resistance to corrosion is insufficient.
The comparison alloy 2 (almost corresponding to the composition range described in Japanese Patent Laid-Open Publication No.9-170402 alloys 1 to 3 of the present invention, contains much Cr and littleAl and W, so that the strength is insufficient.
Further, the comparison alloy 3 (almost corresponding to the composition range described in Japanese Patent Laid-Open Publication No.5-59473 alloys 1 to 3 of the present invention, contains much Mo, so that the resistance to corrosion is insufficient. - Although the invention has been described in its preferred embodiment with a certain degree of particularity, obviously many changes and variations are possible therein. It is therefore to be understood that the present invention may be practiced otherwise than as specifically described herein without departing from the scope and spirit thereof.
Claims (6)
- A Ni-base superalloy consisting of:by weight %, Co: 9 to 11%, Cr: 9 to 12%, Mo: up to 1%, W: 6 to 9%, Al: 4 to 5%, Ti: 4 to 5%, Nb: up to 1%, Ta: up to 3%, Hf: 0.5 to 2.5%, Re: up to 3%, C: 0.05 to 0.15%, B: 0.005 to 0.015%, Zr: up to 0.05%, and the balance of Ni and inevitable impurities.
- A Ni-base superalloy according to claim 1 consisting of:by weight %, Co: 9 to 10%, Cr: 9 to 10%, Mo: 0.5 to 1%, W: 6 to 8%, Al: 4 to 5%, Ti: 4 to 5%, Ta: 2 to 3%, Hf: 0.5 to 2.5%, Re: 1 to 3%, C: 0.05 to 0.1%, B: 0.005 to 0.01%, Zr: up to 0.02%, and the balance of Ni and inevitable impurities.
- A Ni-base superalloy according to claim 1 consisting of:by weight %, Co: 10 to 11%, Cr: 10 to 12%, W: 8 to 9%, Al: 4 to 5%, Ti: 4 to 5%, Nb: up to 1%, Hf: 0.5 to 2.5%, C: 0.05 to 0.15%, B: 0.005 to 0.015%, Zr: 0.01 to 0.05%, and the balance of Ni and inevitable impurities.
- A Ni-base superalloy according to any one of Claims 1 to 3, wherein said weight % of Hf is 0.5 to 1%.
- A gas turbine component characterized in that it is manufactured by using said Ni-base superalloy as defined in any one of Claims 1 to 4.
- A gas turbine component according to Claim 5, wherein said gas turbine component is manufactured by a directional solidification casting method.
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JP2003435037 | 2003-12-26 | ||
PCT/JP2004/019094 WO2005064027A1 (en) | 2003-12-26 | 2004-12-21 | Nickel-based super-heat-resistant alloy and gas turbine component using same |
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EP1715068A1 EP1715068A1 (en) | 2006-10-25 |
EP1715068A4 EP1715068A4 (en) | 2009-11-11 |
EP1715068B1 true EP1715068B1 (en) | 2012-08-01 |
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US (2) | US20080008618A1 (en) |
EP (1) | EP1715068B1 (en) |
JP (1) | JP4911753B2 (en) |
WO (1) | WO2005064027A1 (en) |
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US8615294B2 (en) * | 2008-08-13 | 2013-12-24 | Bio Control Medical (B.C.M.) Ltd. | Electrode devices for nerve stimulation and cardiac sensing |
US20090041615A1 (en) * | 2007-08-10 | 2009-02-12 | Siemens Power Generation, Inc. | Corrosion Resistant Alloy Compositions with Enhanced Castability and Mechanical Properties |
US20100034692A1 (en) * | 2008-08-06 | 2010-02-11 | General Electric Company | Nickel-base superalloy, unidirectional-solidification process therefor, and castings formed therefrom |
EP2823074A4 (en) | 2012-03-09 | 2016-01-13 | Indian Inst Scient | Nickel- aluminium- zirconium alloys |
ITUA20161551A1 (en) * | 2016-03-10 | 2017-09-10 | Nuovo Pignone Tecnologie Srl | LEAGUE HAVING HIGH RESISTANCE TO OXIDATION AND APPLICATIONS OF GAS TURBINES THAT USE IT |
GB2554898B (en) * | 2016-10-12 | 2018-10-03 | Univ Oxford Innovation Ltd | A Nickel-based alloy |
RU2633679C1 (en) * | 2016-12-20 | 2017-10-16 | Федеральное государственное унитарное предприятие "Всероссийский научно-исследовательский институт авиационных материалов" (ФГУП "ВИАМ") | Cast heat-resistant nickel-based alloy and product made thereof |
CN115572861B (en) * | 2022-09-23 | 2024-02-23 | 北京北冶功能材料有限公司 | Nickel-based superalloy easy to machine and form and preparation method and application thereof |
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DE2333775C3 (en) * | 1973-06-27 | 1978-12-14 | Avco Corp., Cincinnati, Ohio (V.St.A.) | Process for the heat treatment of a nickel alloy |
JP3402603B2 (en) | 1986-03-27 | 2003-05-06 | ゼネラル・エレクトリック・カンパニイ | Nickel-base-superalloy with improved low angle grain boundary resistance for producing single crystal products |
US5240518A (en) * | 1990-09-05 | 1993-08-31 | General Electric Company | Single crystal, environmentally-resistant gas turbine shroud |
JP2843476B2 (en) | 1992-03-09 | 1999-01-06 | 日立金属株式会社 | High corrosion resistant high strength superalloy, high corrosion resistant high strength single crystal casting, gas turbine and combined cycle power generation system |
EP0637476B1 (en) * | 1993-08-06 | 2000-02-23 | Hitachi, Ltd. | Blade for gas turbine, manufacturing method of the same, and gas turbine including the blade |
US5451142A (en) * | 1994-03-29 | 1995-09-19 | United Technologies Corporation | Turbine engine blade having a zone of fine grains of a high strength composition at the blade root surface |
JPH07300639A (en) | 1994-04-28 | 1995-11-14 | Toshiba Corp | Highly corrosion resistant nickel-base single crystal superalloy and its production |
JPH09170402A (en) | 1995-12-20 | 1997-06-30 | Hitachi Ltd | Nozzle for gas turbine and manufacture thereof, and gas turbine using same |
JP3246376B2 (en) | 1997-01-23 | 2002-01-15 | 三菱マテリアル株式会社 | Columnar crystal Ni-base heat-resistant alloy large casting with excellent high-temperature intergranular corrosion resistance |
JP4003318B2 (en) * | 1998-10-30 | 2007-11-07 | 株式会社Ihi | Nickel-based single crystal superalloy |
EP1204776B1 (en) * | 1999-07-29 | 2004-06-02 | Siemens Aktiengesellschaft | High-temperature part and method for producing the same |
KR100862346B1 (en) * | 2000-02-29 | 2008-10-13 | 제너럴 일렉트릭 캄파니 | Nickel base superalloys and turbine components fabricated therefrom |
EP1211335B1 (en) | 2000-11-30 | 2007-05-09 | ONERA (Office National d'Etudes et de Recherches Aérospatiales) | Nickel based superalloy having a very high resistance to hot corrosion for single crystal turbine blades of industrial turbines |
RU2215804C2 (en) * | 2001-10-08 | 2003-11-10 | Государственное предприятие "Всероссийский научно-исследовательский институт авиационных материалов" | Nickel-base heat-resistant alloy and article made of thereof |
-
2004
- 2004-12-21 JP JP2005516587A patent/JP4911753B2/en active Active
- 2004-12-21 EP EP04807451A patent/EP1715068B1/en active Active
- 2004-12-21 WO PCT/JP2004/019094 patent/WO2005064027A1/en active Application Filing
- 2004-12-21 US US10/584,244 patent/US20080008618A1/en not_active Abandoned
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EP1715068A4 (en) | 2009-11-11 |
US20080008618A1 (en) | 2008-01-10 |
EP1715068A1 (en) | 2006-10-25 |
JPWO2005064027A1 (en) | 2007-12-20 |
US20100047110A1 (en) | 2010-02-25 |
WO2005064027A1 (en) | 2005-07-14 |
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