EP0186797B1 - Superalliage à base de cobalt et pièces moulées et soudées pour turbines à gaz industrielles fabriquées avec cet alliage - Google Patents

Superalliage à base de cobalt et pièces moulées et soudées pour turbines à gaz industrielles fabriquées avec cet alliage Download PDF

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Publication number
EP0186797B1
EP0186797B1 EP85115301A EP85115301A EP0186797B1 EP 0186797 B1 EP0186797 B1 EP 0186797B1 EP 85115301 A EP85115301 A EP 85115301A EP 85115301 A EP85115301 A EP 85115301A EP 0186797 B1 EP0186797 B1 EP 0186797B1
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EP
European Patent Office
Prior art keywords
cobalt
gas turbine
superalloy
industrial gas
base superalloy
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Expired
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EP85115301A
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German (de)
English (en)
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EP0186797A1 (fr
Inventor
John Stuart Haydon
Adrian Maurice Beltran
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General Electric Co
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General Electric Co
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Publication date
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Publication of EP0186797A1 publication Critical patent/EP0186797A1/fr
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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
    • C22C19/07—Alloys based on nickel or cobalt based on cobalt

Definitions

  • Cobalt-base superalloys having special utility in the production of industrial gas turbine hot gas path components because of their unique combination or properties including excellent hot corrosion resistance, creep rupture strength at high temperature, metallurgical stability, tensile ductility and weldability, are comprised of 0.3 to 0.6% carbon, 27-35% chromium, 9-16% nickel, 6-9% tungsten, 0.45 to 2.0% tantalum, up to 3.0% hafnium, up to 0.1 % niobium, up to 0.7% zirconium, not more than 2.0% iron, 1.5% manganese and silicon and 0.05% boron, balance cobalt and impurities, the carbide formers being selected to satisfy the following equation:
  • 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 US-A-3,383,205 have superior oxidation and hot 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 superalloys either to oxidation or to hot corrosion.
  • 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 is comprised 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 % niobium, manganese and silicon, up to .05% boron, up to 2.0% iron, remainder cobalt plus impurities.
  • 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 immediatley above. Also, 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 in 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. This has significant implication for cast as well as fabricated industrial gas turbine components as it would obviously be highly desirable to be able to weld repair industrial gas turbine nozzles to avoid the time and expense of replacement. Gaining this advantage without forfeiting any other constitutes an important advance in the art. Likewise, the opportunity to build industrial gas turbine combustion chamber structures by welding preformed sheets or plates together which is enabled as a result of this invention, its alloys having excellent weldability, is an important new advance in the production of industrial gas turbines. In our practice of such welding operations as these we prefer to use the gas tungsten arc technique and equipment in general use in industry in the fabrication of both ferrous and nonferrous metal structures, including those of cobalt-base superalloys.
  • 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 and fixed tightly thereto.
  • the superalloys of this invention (Examples II and Example IIIC) 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)

Claims (5)

1. Superalliage à base de cobalt, caractérisé en ce qu'il comprend, en poids
Figure imgb0013
le reste étant du cobalt plus dans impuretés, le carbone (C), le tantale (Ta), l'hafnium (Hf), le titane (Ti), le niobium (Nb) et le zirconium (Zr) étant choisis de façon à satisfaire à l'équation suivante:
Figure imgb0014
2. Superalliage à base de cobalt de la revendication 1, dans lequel le support des pourcentages atomiques des éléments de carburation au carbone est d'environ 0,65.
3. Superalliage à base de cobalt de la revendication 1, contenant environ 0,35% de carbone, environ 29% de chrome, environ 10% de nickel, environ 7% de tungstène, environ 0,5% de zirconium, environ 0,2% de titane, moins de 0,01% de manganèse, moins de 0,07% de silicium, environ 1,0% de tantale, moins d'environ 0,4% de fer, environ 0,5% d'hafnium, le reste étant essentiellement constitué de cobalt et d'impurétés.
4. Tuyère de turbine à gaz industrielle, caractérisée en ce qu'elle est faite du superalliage selon l'une quelconque des revendications précédentes.
5. Pièce de raccordement de turbine à gaz industrielle fabriquée en superalliage à base de cobalt comprenant plusieurs plaques laminées et façonnées à une forme prédéterminée et assemblées et soudées ensemble pour constituer la pièce, caractérisée en ce que le superalliage est comme défini dans l'une quelconque des revendications 1 à 3.
EP85115301A 1984-12-04 1985-12-03 Superalliage à base de cobalt et pièces moulées et soudées pour turbines à gaz industrielles fabriquées avec cet alliage Expired EP0186797B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US67811884A 1984-12-04 1984-12-04
US678118 1984-12-04

Publications (2)

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EP0186797A1 EP0186797A1 (fr) 1986-07-09
EP0186797B1 true EP0186797B1 (fr) 1989-06-21

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EP85115301A Expired EP0186797B1 (fr) 1984-12-04 1985-12-03 Superalliage à base de cobalt et pièces moulées et soudées pour turbines à gaz industrielles fabriquées avec cet alliage

Country Status (6)

Country Link
EP (1) EP0186797B1 (fr)
JP (1) JPS61149450A (fr)
CN (1) CN1011984B (fr)
DE (1) DE3571146D1 (fr)
IN (1) IN164571B (fr)
NO (1) NO166542C (fr)

Families Citing this family (9)

* Cited by examiner, † Cited by third party
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
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
EP4000767A1 (fr) * 2018-11-06 2022-05-25 Hamilton Sundstrand Corporation Formation par pulvérisation à froid
EP3677697A1 (fr) * 2019-01-07 2020-07-08 Siemens Aktiengesellschaft Alliage de cobalt et procédé de fabrication additive

Family Cites Families (8)

* Cited by examiner, † Cited by third party
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
US3582320A (en) * 1969-12-22 1971-06-01 Robert B Herchenroeder Cobalt base alloy
US3933484A (en) * 1974-05-31 1976-01-20 Owens-Corning Fiberglas Corporation Cobalt-base alloy
JPS5582741A (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
JPS5582743A (en) * 1978-12-15 1980-06-21 Hitachi Ltd High-strength high-toughness cobalt alloy

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Publication number Publication date
IN164571B (fr) 1989-04-15
NO854859L (no) 1986-06-05
CN85109085A (zh) 1986-08-20
NO166542B (no) 1991-04-29
NO166542C (no) 1991-08-07
CN1011984B (zh) 1991-03-13
JPS61149450A (ja) 1986-07-08
DE3571146D1 (en) 1989-07-27
EP0186797A1 (fr) 1986-07-09
JPH0459378B2 (fr) 1992-09-22

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