EP0186797A1 - Superlegierung auf Kobaltbasis und daraus hergestellte gegossene und geschweisste Bauteile für Gasturbinen - Google Patents
Superlegierung auf Kobaltbasis und daraus hergestellte gegossene und geschweisste Bauteile für Gasturbinen Download PDFInfo
- Publication number
- EP0186797A1 EP0186797A1 EP85115301A EP85115301A EP0186797A1 EP 0186797 A1 EP0186797 A1 EP 0186797A1 EP 85115301 A EP85115301 A EP 85115301A EP 85115301 A EP85115301 A EP 85115301A EP 0186797 A1 EP0186797 A1 EP 0186797A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- cobalt
- gas turbine
- carbon
- superalloy
- industrial gas
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
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Classifications
-
- 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
- C22C19/07—Alloys based on nickel or cobalt based on cobalt
Definitions
- This invention relates generally to the superalloy branch of the metallurgical art, and is more specifically concerned with new cobalt-base superalloys having an unique combination of properties and consequent special utility in the production of both cast articles and welded structures, and with novel industrial gas turbine hot gas path components of those new alloys.
- Cobalt-base superalloys disclosed and claimed in U.S. Patent No. 3,383,205 have superior ass33aiaars and het corrosion resistance and as a consequence have long been used extensively in commercial production of industrial gas turbine nozzles.
- one of those superalloys is the current first stage nozzle alloy of the Gas Turbine Division of General Electric Company, the assignee hereof.
- the creep rupture and fatigue strength of that alloy are marginal for new industrial gas turbine nozzle applications and in recognition of that fact, a program was launched to improve those properties without significantly diminishing the resistance of the superalloy either to oxidation or to hot corrosion. While the resulting superalloys met-those objectives as a consequence of their relatively high carbon contents (0.40 to 0.50%), they were still not the answer to the problem because of their inferior weldability and low tensile ductility.
- columbium is preferably not used in vacuum melting practice involving the new superalloys of this invention.
- the present invention is a cobalt-base superalloy having an unique combination of properties at high temperature and consequent special utility in the production of industrial gas turbine hot gas- path components, which alloy consists essentially of 0.3-0.6% carbon, 27-35% chromium, 9-16% nickel, 6-9% tungsten, up to 3% hafnium, .45-2.0% tantalum, up to .7% zirconium, up to .5% titanium, up to 1% columbium, manganese and silicon, up to .05%- boron, up to 2.0% iron, remainder essentially cobalt.
- An additional important requirement is that the carbide-forming elements be so selected as to satisfy the relationship stated above and represented by the following equation:
- the present invention is a cast cobalt-base superalloy industrial gas turbine nozzle consisting of the new alloy-set forth immediately above.
- AIso. in this aspect the invention takes the form of transition pieces and shrouds, and of a fabricated cobalt-base superalloy gas turbine combustion chamber comprising a plurality of sheets of the said new alloy rolled and formed in predetermined shape and assembled and welded together.
- the chromium content of these alloys is preferably targeted at 28-30% in recognition that departures in each direction can penalize alloy properties, specifically amounts less than about 27% result in loss of oxidation and hot corrosion resistance and amounts greater than about 35% result in loss of ductility without offsetting gain in either oxidation resistance or hot corrosion resistance.
- the cast and fabricated bodies of this invention being components of industrial gas turbines are quite different from aircraft jet engine components especially iin respect to size and mass. Because of this, they represent problems unlike those of the relatively lighter weight counterparts such as marked cracking tendency associated with welding operations.
- the first stage nozzle 10 of an industrial gas turbine shown in Fig. 1 is a casting of our preferred alloy composition produced by the injection molding and investment casting technique in general use in the art. Also, the shape and size and the design details of nozzle 10 essentially duplicate those features of the present standard first stage nozzle. Transition piece 20 similarly resembles that which has long been in general use in industrial gas turbines differing importantly, however, in that it is constructed of parts of an alloy of this invention welded together to provide a strong crack-free assembly of integrally bonded elements. Thus, bracket 22 is fitted in place on body 23 and welded securely an fluid tightly thereto.
- the superalloys of this invention have ultimate tensile strengths equal to or better than the commercial superalloy of Example I and have creep rupture strength substantially greater than that commercial superalloy. Further it is apparent from Table I that these new superalloys have good room temperature tensile elongation characteristics and as Table II shows and Fig. 3 graphically illustrates, the weldability of the superalloys of this invention is superior to commercial superalloys A and E and even spectacularly so in the case of the superalloy of Example II which as indicated above is our present preferred embodiment of the invention.
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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)
- Materials For Medical Uses (AREA)
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US67811884A | 1984-12-04 | 1984-12-04 | |
US678118 | 1984-12-04 |
Publications (2)
Publication Number | Publication Date |
---|---|
EP0186797A1 true EP0186797A1 (de) | 1986-07-09 |
EP0186797B1 EP0186797B1 (de) | 1989-06-21 |
Family
ID=24721479
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP85115301A Expired EP0186797B1 (de) | 1984-12-04 | 1985-12-03 | Superlegierung auf Kobaltbasis und daraus hergestellte gegossene und geschweisste Bauteile für Gasturbinen |
Country Status (6)
Country | Link |
---|---|
EP (1) | EP0186797B1 (de) |
JP (1) | JPS61149450A (de) |
CN (1) | CN1011984B (de) |
DE (1) | DE3571146D1 (de) |
IN (1) | IN164571B (de) |
NO (1) | NO166542C (de) |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2769024A1 (fr) * | 1997-09-29 | 1999-04-02 | Saint Gobain Isover | Alliage a base de cobalt, article realise a partir de l'alliage et son procede de fabrication |
US8252376B2 (en) * | 2001-04-27 | 2012-08-28 | Siemens Aktiengesellschaft | Method for restoring the microstructure of a textured article and for refurbishing a gas turbine blade or vane |
US20200139435A1 (en) * | 2018-11-06 | 2020-05-07 | Hamilton Sundstrand Corporation | Cold spray forming |
Families Citing this family (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US7947933B2 (en) | 2003-11-25 | 2011-05-24 | Kyocera Corporation | Ceramic heater and method for manufacture thereof |
US6983599B2 (en) * | 2004-02-12 | 2006-01-10 | General Electric Company | Combustor member and method for making a combustor assembly |
US20070017906A1 (en) * | 2005-06-30 | 2007-01-25 | General Electric Company | Shimmed laser beam welding process for joining superalloys for gas turbine applications |
CN102021558B (zh) * | 2009-09-09 | 2012-07-11 | 沈阳大陆激光技术有限公司 | 用于循环流化床锅炉水冷壁管激光熔覆涂层的合金粉末 |
CN108070742A (zh) * | 2016-11-15 | 2018-05-25 | 中国科学院金属研究所 | 一种燃气轮机导向叶片用钴基高温合金及其制备方法和应用 |
EP3677697A1 (de) * | 2019-01-07 | 2020-07-08 | Siemens Aktiengesellschaft | Co-legierung zur generativen fertigung und verfahren |
Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB891550A (en) * | 1959-08-28 | 1962-03-14 | Sierra Metals Corp | Metal alloys |
US3383205A (en) * | 1964-12-14 | 1968-05-14 | Gen Electric | Cobalt base alloys |
US3549356A (en) * | 1969-01-06 | 1970-12-22 | Gen Electric | High temperature corrosive resistant cobalt-base alloys |
FR2074104A5 (de) * | 1969-12-22 | 1971-10-01 | Cabot Corp | |
FR2273075A1 (de) * | 1974-05-31 | 1975-12-26 | Owens Corning Fiberglass Corp |
Family Cites Families (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPS5582741A (en) * | 1978-12-15 | 1980-06-21 | Hitachi Ltd | High-strength high-toughness cobalt alloy |
JPS5582743A (en) * | 1978-12-15 | 1980-06-21 | Hitachi Ltd | High-strength high-toughness cobalt alloy |
JPS5582744A (en) * | 1978-12-15 | 1980-06-21 | Hitachi Ltd | High-strength high-toughness cobalt alloy |
-
1985
- 1985-11-14 CN CN85109085A patent/CN1011984B/zh not_active Expired
- 1985-11-18 IN IN818/CAL/85A patent/IN164571B/en unknown
- 1985-11-28 JP JP60266298A patent/JPS61149450A/ja active Granted
- 1985-12-03 EP EP85115301A patent/EP0186797B1/de not_active Expired
- 1985-12-03 NO NO854859A patent/NO166542C/no unknown
- 1985-12-03 DE DE8585115301T patent/DE3571146D1/de not_active Expired
Patent Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB891550A (en) * | 1959-08-28 | 1962-03-14 | Sierra Metals Corp | Metal alloys |
US3383205A (en) * | 1964-12-14 | 1968-05-14 | Gen Electric | Cobalt base alloys |
US3549356A (en) * | 1969-01-06 | 1970-12-22 | Gen Electric | High temperature corrosive resistant cobalt-base alloys |
FR2074104A5 (de) * | 1969-12-22 | 1971-10-01 | Cabot Corp | |
FR2273075A1 (de) * | 1974-05-31 | 1975-12-26 | Owens Corning Fiberglass Corp |
Cited By (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2769024A1 (fr) * | 1997-09-29 | 1999-04-02 | Saint Gobain Isover | Alliage a base de cobalt, article realise a partir de l'alliage et son procede de fabrication |
WO1999016919A1 (fr) * | 1997-09-29 | 1999-04-08 | Isover Saint-Gobain | Alliage a base de cobalt, article realise a partir de l'alliage et son procede de fabrication |
CN1094522C (zh) * | 1997-09-29 | 2002-11-20 | 伊索福圣戈班公司 | 钴基合金,由该合金制得的制品 |
US8252376B2 (en) * | 2001-04-27 | 2012-08-28 | Siemens Aktiengesellschaft | Method for restoring the microstructure of a textured article and for refurbishing a gas turbine blade or vane |
US20200139435A1 (en) * | 2018-11-06 | 2020-05-07 | Hamilton Sundstrand Corporation | Cold spray forming |
Also Published As
Publication number | Publication date |
---|---|
JPH0459378B2 (de) | 1992-09-22 |
NO854859L (no) | 1986-06-05 |
CN85109085A (zh) | 1986-08-20 |
JPS61149450A (ja) | 1986-07-08 |
NO166542C (no) | 1991-08-07 |
IN164571B (de) | 1989-04-15 |
DE3571146D1 (en) | 1989-07-27 |
EP0186797B1 (de) | 1989-06-21 |
CN1011984B (zh) | 1991-03-13 |
NO166542B (no) | 1991-04-29 |
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