WO2005064027A1 - Ni基超耐熱合金及びそれを用いたガスタービン部品 - Google Patents
Ni基超耐熱合金及びそれを用いたガスタービン部品 Download PDFInfo
- Publication number
- WO2005064027A1 WO2005064027A1 PCT/JP2004/019094 JP2004019094W WO2005064027A1 WO 2005064027 A1 WO2005064027 A1 WO 2005064027A1 JP 2004019094 W JP2004019094 W JP 2004019094W WO 2005064027 A1 WO2005064027 A1 WO 2005064027A1
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- Prior art keywords
- alloy
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- gas turbine
- temperature
- resistant alloy
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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 (nickel) -based super heat-resistant alloy having excellent high-temperature corrosion resistance, high-temperature oxidation resistance, and high-temperature strength in order to cope with low-quality fuel, and a gas turbine component using the same.
- Ni-base super heat-resistant alloys are widely used as components of industrial gas turbines, for example, blade materials, Rene80 and IN792, which have excellent corrosion resistance, and Mar-M, which has excellent oxidation resistance and high strength.
- CMSX-11 which achieves both corrosion resistance and strength by single crystallizing an alloy with a high Cr (chromium) content!
- alloys with high corrosion resistance and strength that are made parallel by single crystallizing an alloy with a high Cr content have insufficient oxidation resistance and are single-crystal materials, making them complex. There is a problem that the production yield of shaped parts is reduced.
- the P value calculated by weight (%) according to equation (1) is 2350-3280,
- High corrosion-resistant and high-strength alloys made of M are known.
- Ni-based superalloy has insufficient oxidation resistance because it contains too much Cr.
- Ni-based superalloys having Hf of 2% or less, C of 0.03 to 0.25%, and of B of 0.002 to 0.05%, with the remaining components being Ni and incidental impurities, are known.
- Ni-base superalloy does not consider the relationship with elements added for improving strength, which is said to improve the balance between oxidation resistance and corrosion resistance by increasing the A1 to Ti ratio.
- weight 0/0, Cr2- 25%, All- 7%, W2- 15%, TiO. 5-5%, Nb3% hereinafter, MO6% or less, Tal- 12%, less Re4% , Co7.5-25%, Fe (iron) 0.5% or less, CO. 2% or less, BO.002-0.035%, Hf 2.0 or less, ZrO. 02%, and Ni of 40% or more Ni-based alloys are known!
- Ni-based alloy does not consider the relationship between the balance of the amounts of each element and the material properties.
- Japanese Patent No. 2843476, Japanese Patent No. 3246376, Japanese Patent Application Laid-Open No. 2002-235135, Japanese Patent Application Laid-Open No. 7-300639, Japanese Patent Application JP-A-5-59473 and JP-A-9-170402 are examples.
- the present invention provides excellent high-temperature corrosion resistance for low-quality fuel, high-temperature oxidation resistance and high-temperature strength for high-efficiency thermal efficiency as a component material for industrial gas turbines. It is an object of the present invention to provide a Ni-based super heat-resistant alloy capable of securing a high yield in a precision manufacturing process and a gas turbine component using the same.
- the first Ni-based super heat-resistant alloy according to the present invention comprises, by weight%, Co9-11%, Cr9-12%, Mol% or less, W6-9%, A14-5. %, Ti4-5%, Nbl% or less, Ta3% or less, HfO.5-2.5%, Re3% or less, CO.05-0.15%, BO.005-0.015%, ZrO. 05%
- the following and the balance are characterized by being composed of Ni and unavoidable impurities.
- the weight percentage of Hf is 0.5-1%.
- a second Ni-based super heat-resistant alloy according to the present invention comprises, by weight%, Co9-10%, Cr9-10%, MoO. 5-1%, W6-8%, A14—5%, Ti4—5%, Ta2—3%, HfO. 5—2.5%, Rel—3%, C0. 05—0.1%, B0. 005—0.01%, Zr0 .2% or less, with the balance being Ni and inevitable impurity power.
- the weight percentage of Hf is 0.5-1%.
- the third Ni-base superalloy according to the present invention comprises, by weight%, ColO—11%, CrlO—12%, W8—9%, A14—5%, Ti4 5%, Nbl% or less, Hf 0.5-2.5%, CO.05-0.15%, BO.005-0.015%, ZrO.01-0.05%, the balance being Ni and unavoidable impurity power .
- the weight percentage of Hf is 0.5-1%.
- the gas turbine component according to the present invention is manufactured by using any one of the first to third Ni-based super heat-resistant alloys, preferably by a unidirectional solidification method. It is characterized by being manufactured.
- the present invention in order to make high-temperature corrosion resistance, high-temperature oxidation resistance, and high-temperature strength comparable, a large number of alloys are trial-produced and evaluated, and as a result, the Cr A1—Ti content falls within an appropriate range.
- W was found to be effective as an element that contributes to strength improvement and has little adverse effect on corrosion resistance in the composition range, and furthermore, it has been added to the ⁇ (gamma) phase and ⁇ ′ (gamma prime) phase. Solid capacity capacity was determined in consideration of the determined organizational stability.
- the amount ratio of Ti, which contributes to corrosion resistance becomes an appropriate range, and by adding the strengthening element centering on W, the addition amount is determined in consideration of the contribution to strength improvement and the effect on corrosion resistance. It can be excellent in high-temperature corrosion resistance, high-temperature oxidation resistance and high-temperature strength.
- the second Ni-base superalloy is suitable for columnar crystal wings or single crystal wings formed by unidirectional solidification, can exhibit a high level of corrosion resistance, oxidation resistance, and strength.
- the heat-resistant alloy is suitable for a polycrystal blade formed by a normal structure or a columnar crystal blade formed by a unidirectional solidification structure, and can suppress the material cost while maintaining the characteristics of corrosion resistance, oxidation resistance, and strength. Therefore, application to a moving blade of an industrial gas turbine compatible with low-quality fuel is effective in improving the thermal efficiency and reliability of the gas turbine.
- the allowable range of the reduction in strength due to structural defects such as low-angle grain boundaries and high-angle grain boundaries is wider, so that the High efficiency and a high yield can be ensured in the process of manufacturing gas turbine components having various shapes.
- FIG. 1 is an explanatory view showing the results of a high-temperature corrosion test of a Ni-base superalloy of the present invention and an existing Ni-base superalloy.
- FIG. 2 is an explanatory view showing the results of a high-temperature oxidation test of a Ni-base superalloy of the present invention and an existing Ni-base superalloy.
- FIG. 3 is an explanatory diagram showing the results of a creep test of a Ni-base superalloy of the present invention and an existing Ni-base superalloy.
- Co increases the solution heat treatment temperature range. However, if the content is less than 9 wt% (10 wt% in the third alloy), the effect cannot be obtained, and l lwt% (second If it exceeds 10 wt% in alloys, the precipitation of the ⁇ 'phase decreases and the high-temperature strength decreases.
- Cr improves the corrosion resistance especially in an environment where sulfide-acid sulfide is combined, but the content is 9 wt%.
- Mo improves the high-temperature strength by solid solution strengthening and precipitation hardening. However, if the content exceeds lwt%, the corrosion resistance decreases.
- W improves the high-temperature strength by solid solution strengthening and precipitation hardening. However, if the content is less than 6 wt% (8 wt% in the third alloy), the effect cannot be obtained, and 9 wt% ( If alloy 2 exceeds 8 wt%), a TCP phase is formed and the high-temperature strength decreases.
- W is generally considered to lower the corrosion resistance, but it was found that the adverse effect on the corrosion resistance was small in the composition range of the present invention.
- A1 forms a ⁇ 'phase and improves high-temperature strength and improves oxidation resistance. However, if the content is less than 4 wt%, the effect cannot be obtained, and the content exceeds 5 wt%. In addition, the eutectic ⁇ 'phase becomes large, so that the solution heat treatment becomes difficult and the corrosion resistance decreases.
- Ti has a power to improve corrosion resistance of less than 4 wt%, the effect cannot be obtained. If it exceeds 5 wt%, oxidation resistance and heat treatment properties are reduced. [0026] Nb forms a solid solution in the ⁇ 'phase and enhances high-temperature strength. When the content exceeds 1%, the Nb is biased toward crystal grain boundaries and the high-temperature strength decreases.
- Ta improves the high-temperature strength by solid solution strengthening and precipitation hardening. However, if the content exceeds 3 wt%, the eutectic ⁇ 'phase becomes large, and the solution heat treatment becomes difficult.
- the Ta content is less than 2 wt%, the above effects cannot be obtained.
- Hf strengthens the grain boundaries to improve high-temperature strength and ductility, and its effect is less than 0.5 wt% when the force content that is effective for the grain boundary cracking during DS alloy formation is less than 0.5 wt%. Not obtained, 2.5wt
- the high-temperature strength decreases due to bias toward the crystal grain boundaries.
- Re increases the high-temperature strength by solid solution strengthening and improves corrosion resistance, particularly at temperatures of 900 ° C or higher.
- content exceeds 3 wt%, ductility is hindered by precipitation of the TCP phase.
- specific gravity is large and expensive.
- B forms borides and strengthens grain boundaries, but when the content is less than 0.005 wt%.
- Zr when its content for strengthening the grain boundary exceeds 0.05 wt% (0.02 wt% for the second alloy), ductility and toughness decrease, lowering the melting point of the grain boundary and increasing the high-temperature strength. Decreases.
- the above effects cannot be obtained.
- Ni-base superalloys having the component compositions shown in Table 1 (along with the component compositions of existing alloy 1 (Rene80H) and existing alloy 2 (Mar-M247)) (alloys 113 of the present invention and comparative alloys 11) 3) were prepared, and each of these Ni-base superalloys was subjected to a unidirectional solidification Solidification was performed under the conditions of mmZh to produce a round bar-shaped columnar crystal product. Next, the following heat treatment was performed to obtain respective Ni-base super heat-resistant alloys. Heat treatment conditions
- Test conditions In combustion gas obtained by adding corrosive components (sulfurized oil, artificial seawater) to kerosene fuel, combustion gas temperature 1050 ° C, air cooling after exposure for 100 hours, repeated 5 times (500 hours in total)
- Test conditions air, 950 ° C, air-cooled after 500 hours exposure
- Test conditions air, 900. C, 392MPa
- the comparative alloys 13 and the existing alloy 2 Table 2 shows the results of examining the fracture life ratios.
- the alloy 1 of the present invention has excellent corrosion resistance, oxidation resistance, and strength, and is particularly suitable for use as a unidirectional solidified material in which strength is emphasized.
- the alloy 2 of the present invention is suitable for use under conditions where importance is placed on oxidation resistance and strength, and the corrosion resistance is within the allowable range for fuel oil A fuel. Further, the alloy 3 of the present invention is suitable for use under conditions that emphasize corrosion resistance.
- the existing alloy 1 is widely used as a gas turbine blade material and has excellent corrosion resistance, but has a larger amount of Cr and a smaller amount of A1 compared to the composition range of the alloys 13 to 13 of the present invention.
- it cannot cope with high-temperature gas-riding of combustion gas for the purpose of improving thermal efficiency with low oxidation resistance.
- the existing alloy 2 has excellent oxidation resistance and strength, but has a low Cr and Ti content and a high A1 content compared to the composition range of the alloys 13 of the present invention. I can not cope.
- Comparative Alloy 1 (approximately corresponding to the composition range described in JP-A-5-59473 and JP-A-9-170402) was compared with the composition range of the alloy 13 of the present invention. Therefore, the corrosion resistance is insufficient due to low Ti content.
- Comparative alloy 2 (approximately falling within the composition range described in Japanese Patent Application Laid-Open No. 9-170402) contains more Cr and less A1 and W than the composition range of Alloy 13 of the present invention. Insufficient degree.
- Comparative Alloy 3 (approximately corresponding to the composition range described in Japanese Patent Application Laid-Open No. 5-59473) has a higher Mo content than the composition range of Alloy 13 of the present invention, and therefore has insufficient corrosion resistance.
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- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
Claims
Priority Applications (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP04807451A EP1715068B1 (en) | 2003-12-26 | 2004-12-21 | Nickel-based super-heat-resistant alloy and gas turbine component using same |
US10/584,244 US20080008618A1 (en) | 2003-12-26 | 2004-12-21 | Ni-Base Superalloy and Gas Turbine Component Using the Same |
JP2005516587A JP4911753B2 (ja) | 2003-12-26 | 2004-12-21 | Ni基超耐熱合金及びそれを用いたガスタービン部品 |
US12/585,184 US20100047110A1 (en) | 2003-12-26 | 2009-09-08 | Ni-base superalloy and gas turbine component using the same |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP2003-435037 | 2003-12-26 | ||
JP2003435037 | 2003-12-26 |
Related Child Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US12/585,184 Continuation US20100047110A1 (en) | 2003-12-26 | 2009-09-08 | Ni-base superalloy and gas turbine component using the same |
Publications (1)
Publication Number | Publication Date |
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WO2005064027A1 true WO2005064027A1 (ja) | 2005-07-14 |
Family
ID=34736583
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/JP2004/019094 WO2005064027A1 (ja) | 2003-12-26 | 2004-12-21 | Ni基超耐熱合金及びそれを用いたガスタービン部品 |
Country Status (4)
Country | Link |
---|---|
US (2) | US20080008618A1 (ja) |
EP (1) | EP1715068B1 (ja) |
JP (1) | JP4911753B2 (ja) |
WO (1) | WO2005064027A1 (ja) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2010037658A (ja) * | 2008-08-06 | 2010-02-18 | General Electric Co <Ge> | ニッケル基超合金、その一方向凝固プロセス並びに得られる鋳造品 |
Families Citing this family (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
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 |
EP2823074A4 (en) | 2012-03-09 | 2016-01-13 | Indian Inst Scient | NICKEL-ALUMINUM-ZIRCONIUM ALLOYS |
ITUA20161551A1 (it) * | 2016-03-10 | 2017-09-10 | Nuovo Pignone Tecnologie Srl | Lega avente elevata resistenza all’ossidazione ed applicazioni di turbine a gas che la impiegano |
GB2554898B (en) * | 2016-10-12 | 2018-10-03 | Univ Oxford Innovation Ltd | A Nickel-based alloy |
RU2633679C1 (ru) * | 2016-12-20 | 2017-10-16 | Федеральное государственное унитарное предприятие "Всероссийский научно-исследовательский институт авиационных материалов" (ФГУП "ВИАМ") | Литейный жаропрочный сплав на никелевой основе и изделие, выполненное из него |
CN115572861B (zh) * | 2022-09-23 | 2024-02-23 | 北京北冶功能材料有限公司 | 一种易于加工成型的镍基高温合金及其制备方法和应用 |
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JPH0559473A (ja) | 1986-03-27 | 1993-03-09 | General Electric Co <Ge> | 単結晶製品を製造するための改善された低角粒界耐性を有するニツケル基―超合金 |
JPH07300639A (ja) | 1994-04-28 | 1995-11-14 | Toshiba Corp | 高耐食性ニッケル基単結晶超合金およびその製造方法 |
JPH09170402A (ja) | 1995-12-20 | 1997-06-30 | Hitachi Ltd | ガスタービン用ノズル及びその製造法とそれを用いたガスタービン |
JP2843476B2 (ja) | 1992-03-09 | 1999-01-06 | 日立金属株式会社 | 高耐食高強度超合金、高耐食高強度単結晶鋳造物、ガスタービンおよびコンバインドサイクル発電システム |
JP2000129381A (ja) * | 1998-10-30 | 2000-05-09 | Ishikawajima Harima Heavy Ind Co Ltd | ニッケル基単結晶超合金 |
JP3246376B2 (ja) | 1997-01-23 | 2002-01-15 | 三菱マテリアル株式会社 | 高温耐粒界腐食性に優れた柱状晶Ni基耐熱合金大型鋳物 |
JP2002235135A (ja) | 2000-11-30 | 2002-08-23 | Howmet Ltd | 産業用タービンの単結晶ブレードのための非常に高い耐高温腐食性をもつニッケル系超合金 |
JP2003529677A (ja) * | 1999-07-29 | 2003-10-07 | シーメンス アクチエンゲゼルシヤフト | 耐熱性の構造部材及びその製造方法 |
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DE2333775C3 (de) * | 1973-06-27 | 1978-12-14 | Avco Corp., Cincinnati, Ohio (V.St.A.) | Verfahren zur Wärmebehandlung einer Nickellegierung |
US5240518A (en) * | 1990-09-05 | 1993-08-31 | General Electric Company | Single crystal, environmentally-resistant gas turbine shroud |
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 |
JP5073905B2 (ja) * | 2000-02-29 | 2012-11-14 | ゼネラル・エレクトリック・カンパニイ | ニッケル基超合金及び該超合金から製造したタービン部品 |
RU2215804C2 (ru) * | 2001-10-08 | 2003-11-10 | Государственное предприятие "Всероссийский научно-исследовательский институт авиационных материалов" | Жаропрочный сплав на основе никеля и изделие, выполненное из него |
-
2004
- 2004-12-21 US US10/584,244 patent/US20080008618A1/en not_active Abandoned
- 2004-12-21 EP EP04807451A patent/EP1715068B1/en active Active
- 2004-12-21 WO PCT/JP2004/019094 patent/WO2005064027A1/ja active Application Filing
- 2004-12-21 JP JP2005516587A patent/JP4911753B2/ja active Active
-
2009
- 2009-09-08 US US12/585,184 patent/US20100047110A1/en not_active Abandoned
Patent Citations (8)
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JPH0559473A (ja) | 1986-03-27 | 1993-03-09 | General Electric Co <Ge> | 単結晶製品を製造するための改善された低角粒界耐性を有するニツケル基―超合金 |
JP2843476B2 (ja) | 1992-03-09 | 1999-01-06 | 日立金属株式会社 | 高耐食高強度超合金、高耐食高強度単結晶鋳造物、ガスタービンおよびコンバインドサイクル発電システム |
JPH07300639A (ja) | 1994-04-28 | 1995-11-14 | Toshiba Corp | 高耐食性ニッケル基単結晶超合金およびその製造方法 |
JPH09170402A (ja) | 1995-12-20 | 1997-06-30 | Hitachi Ltd | ガスタービン用ノズル及びその製造法とそれを用いたガスタービン |
JP3246376B2 (ja) | 1997-01-23 | 2002-01-15 | 三菱マテリアル株式会社 | 高温耐粒界腐食性に優れた柱状晶Ni基耐熱合金大型鋳物 |
JP2000129381A (ja) * | 1998-10-30 | 2000-05-09 | Ishikawajima Harima Heavy Ind Co Ltd | ニッケル基単結晶超合金 |
JP2003529677A (ja) * | 1999-07-29 | 2003-10-07 | シーメンス アクチエンゲゼルシヤフト | 耐熱性の構造部材及びその製造方法 |
JP2002235135A (ja) | 2000-11-30 | 2002-08-23 | Howmet Ltd | 産業用タービンの単結晶ブレードのための非常に高い耐高温腐食性をもつニッケル系超合金 |
Non-Patent Citations (1)
Title |
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See also references of EP1715068A4 * |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2010037658A (ja) * | 2008-08-06 | 2010-02-18 | General Electric Co <Ge> | ニッケル基超合金、その一方向凝固プロセス並びに得られる鋳造品 |
Also Published As
Publication number | Publication date |
---|---|
EP1715068A1 (en) | 2006-10-25 |
EP1715068A4 (en) | 2009-11-11 |
US20080008618A1 (en) | 2008-01-10 |
US20100047110A1 (en) | 2010-02-25 |
EP1715068B1 (en) | 2012-08-01 |
JP4911753B2 (ja) | 2012-04-04 |
JPWO2005064027A1 (ja) | 2007-12-20 |
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