EP0330858B1 - Ausscheidungshärtbare Nickelbasis-Superlegierung mit verbesserten mechanischen Eigenschaften im Temperaturbereich von 600 bis 750oC - Google Patents

Ausscheidungshärtbare Nickelbasis-Superlegierung mit verbesserten mechanischen Eigenschaften im Temperaturbereich von 600 bis 750oC Download PDF

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Publication number
EP0330858B1
EP0330858B1 EP89101901A EP89101901A EP0330858B1 EP 0330858 B1 EP0330858 B1 EP 0330858B1 EP 89101901 A EP89101901 A EP 89101901A EP 89101901 A EP89101901 A EP 89101901A EP 0330858 B1 EP0330858 B1 EP 0330858B1
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EP
European Patent Office
Prior art keywords
rate
heating
argon atmosphere
auf
precipitation
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EP89101901A
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German (de)
English (en)
French (fr)
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EP0330858A1 (de
Inventor
Peter James Dr. Lawrence
Mohamed Dr. Nazmy
Markus Staubli
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ABB Asea Brown Boveri Ltd
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ABB Asea Brown Boveri Ltd
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    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
    • C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
    • C22F1/10—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of nickel or cobalt or alloys based thereon
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • 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

  • Superalloys based on nickel which thanks to their excellent mechanical properties at high temperatures are used in the construction of thermally and mechanically highly stressed thermal machines. Preferred use as blade materials for gas turbines.
  • the invention relates to the further development of nickel-based superalloys with a focus on cast alloys for directional solidification.
  • It also relates to a method for producing a component from the precipitation-hardenable nickel-based superalloy by melting, pouring and pouring the alloy their crystallites are forced to solidify and then subjected to heat treatment.
  • the alloy with the trade name IN 738 from INCO is frequently used. It has the following composition:
  • this alloy does not meet the long-term creep strength requirements placed on industrial gas turbines. In addition, it contains not insignificant amounts of the expensive strategic metal cobalt.
  • the alloy with the trade name IN 792 from INCO should be mentioned as a further commercial nickel-based casting superalloy used in gas turbine construction. It has the following composition:
  • This alloy is also unsatisfactory in terms of its creep behavior under long-term stress. In addition, their corrosion resistance in the temperature range of interest is rather at the lower limit.
  • the invention has for its object to provide a precipitation-hardenable nickel-based superalloy which has improved mechanical properties such as heat resistance, creep limit etc. in the temperature range from 600 ° C to 750 ° C while maintaining sufficient corrosion resistance.
  • the alloy is said to be particularly suitable for cast components with directional solidification for long-term use of over 10,000 hours. It is also an object of the invention to provide a heat treatment for cast components with directed Specify solidification, which guarantees optimal mechanical properties.
  • the nickel-base superalloy mentioned at the outset has the following composition:
  • 1 shows a temperature / time diagram of the heat treatment for a first alloy. 1 is the course of the temperature as a function of time for a gradual solution annealing.
  • the heating up to 1100 ° C is not critical and can be done arbitrarily.
  • a heating rate of 30 ° C / h is maintained from 1100 ° C to 1220 ° C.
  • the temperature of 1220 ° C is maintained for 2 h, then the temperature is raised to 1280 ° C at 30 ° C / h. This temperature is maintained for 10 hours (super solution annealing). Then it is rapidly cooled to room temperature.
  • Line 4 shows the course of the temperature as a function of time for one-stage aging at 850 ° C./24 h, as is usually done in practice instead of the two-stage for the sake of simplicity.
  • FIG. 2 shows a diagram of the heat treatment for a second alloy.
  • the process sequence is the same up to the super solution annealing temperature of 1270 ° C. as that according to FIG. 1.
  • 5 is the temperature as a function of the time for solution annealing, 6 and 7 that for two-stage aging, 8 that for one-stage aging.
  • Curves 6, 7, 8 correspond exactly to curves 2, 3, 4 in FIG. 1.
  • FIG. 3 shows a diagram of the creep behavior of a component made of a first alloy at a temperature of 700 ° C.
  • the results relate to a test rod (tensile test) made from a cast workpiece with directed solidification.
  • 9 is the tensile stress tolerated as a function of the load time until break at a temperature of 700 ° C.
  • the dashed curve refers to extrapolated values.
  • the alloy can withstand approx. 1000 MPa in a short-term test. Measured over 1000 h, the alloy can withstand a tensile load of approx. 700 MPa.
  • a nickel-based superalloy with the following composition was produced:
  • test bars for the creep tests have now been worked out from the heat-treated bars.
  • the test bars had a diameter of 6 mm and a length of 60 mm.
  • the creep tests were carried out under constant tensile stress until breaking at a constant temperature of 700 ° C.
  • the results are shown in curve 9 of FIG. 3. From this representation it can be seen that the values from a load time up to a break of 500 h upwards are approx. 130 MPa higher than that of the commercial alloy IN 738. At the same time until the fracture, the component made from the new alloy can withstand significantly higher loads. If one considers the times to break to be borne with unchanged loading of less than 650 MPa, these are around a power of ten higher for the new alloy than for IN 738. 5000 h instead of just 500 h; 10000 h instead of just 1000 h.
  • a nickel-based superalloy with the following composition was produced:
  • Test rods 6 mm in diameter and 60 mm in length were worked out from the heat-treated rods for the creep tests. The latter were carried out analogously to Example 1 at a temperature of 700 ° C. The results are shown in curve 10 of FIG. 4. The curves 10 (Fig. 4) and 9 (Fig. 3) practically coincide. The statements made in Example 1 apply here in full.
  • the invention is not limited to the exemplary embodiments.
  • the composition of the new precipitation-hardenable nickel-based superalloy is within the following limits:
  • the advantages of the new alloy are the better creep behavior in the temperature range of 600 to 750 ° C compared to commercially available nickel-based casting super alloys.
  • the new alloy permits an increase in the permanent load with the same service life or up to 10 times longer use with an otherwise identical load compared to commercial alloys, and this with sufficient corrosion resistance under the specified conditions of use.

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  • Chemical & Material Sciences (AREA)
  • Mechanical Engineering (AREA)
  • Organic Chemistry (AREA)
  • Metallurgy (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Crystallography & Structural Chemistry (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Manufacture And Refinement Of Metals (AREA)
  • Crystals, And After-Treatments Of Crystals (AREA)
  • Electrolytic Production Of Metals (AREA)
  • Furnace Housings, Linings, Walls, And Ceilings (AREA)
  • Eyeglasses (AREA)
EP89101901A 1988-03-02 1989-02-03 Ausscheidungshärtbare Nickelbasis-Superlegierung mit verbesserten mechanischen Eigenschaften im Temperaturbereich von 600 bis 750oC Expired - Lifetime EP0330858B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH755/88 1988-03-02
CH755/88A CH675256A5 (zh) 1988-03-02 1988-03-02

Publications (2)

Publication Number Publication Date
EP0330858A1 EP0330858A1 (de) 1989-09-06
EP0330858B1 true EP0330858B1 (de) 1992-05-20

Family

ID=4194437

Family Applications (1)

Application Number Title Priority Date Filing Date
EP89101901A Expired - Lifetime EP0330858B1 (de) 1988-03-02 1989-02-03 Ausscheidungshärtbare Nickelbasis-Superlegierung mit verbesserten mechanischen Eigenschaften im Temperaturbereich von 600 bis 750oC

Country Status (8)

Country Link
US (1) US4957703A (zh)
EP (1) EP0330858B1 (zh)
JP (1) JP2825836B2 (zh)
AU (1) AU610996B2 (zh)
CA (1) CA1334632C (zh)
CH (1) CH675256A5 (zh)
DE (1) DE58901443D1 (zh)
NO (1) NO172812C (zh)

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5489346A (en) * 1994-05-03 1996-02-06 Sps Technologies, Inc. Hot corrosion resistant single crystal nickel-based superalloys
JP2905473B1 (ja) 1998-03-02 1999-06-14 科学技術庁金属材料技術研究所長 Ｎｉ基一方向凝固合金の製造方法
ES2269013B2 (es) * 2006-12-01 2007-11-01 Industria De Turbo Propulsores, S.A. Superaleaciones monocristalinas y solidificadas direccionalmente de baja densidad.
JP5038990B2 (ja) * 2008-08-07 2012-10-03 株式会社東芝 ガスタービン部品の熱処理方法及び補修方法並びにガスタービン部品
JP5063550B2 (ja) * 2008-09-30 2012-10-31 株式会社日立製作所 ニッケル基合金及びそれを用いたガスタービン翼
JP5396445B2 (ja) * 2011-08-29 2014-01-22 株式会社日立製作所 ガスタービン

Family Cites Families (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1275562A (fr) * 1960-11-02 1961-11-10 Mond Nickel Co Ltd Alliages résistant au fluage
US3146136A (en) * 1961-01-24 1964-08-25 Rolls Royce Method of heat treating nickel base alloys
US3310440A (en) * 1964-10-21 1967-03-21 United Aircraft Corp Heat treatment of nickel base alloys
FR2374427A1 (fr) * 1976-12-16 1978-07-13 Gen Electric Alliage a base de nickel perfectionne et piece coulee obtenue a partir de cet alliage
CA1117320A (en) * 1977-05-25 1982-02-02 David N. Duhl Heat treated superalloy single crystal article and process
GB2071695A (en) * 1980-03-13 1981-09-23 Rolls Royce An alloy suitable for making single-crystal castings and a casting made thereof
CH654593A5 (de) * 1983-09-28 1986-02-28 Bbc Brown Boveri & Cie Verfahren zur herstellung eines feinkoernigen werkstuecks aus einer nickelbasis-superlegierung.
EP0207874B1 (en) * 1985-05-09 1991-12-27 United Technologies Corporation Substrate tailored coatings for superalloys
JPS6152339A (ja) * 1985-07-16 1986-03-15 Natl Res Inst For Metals Ｎｉ基耐熱合金
US4814023A (en) * 1987-05-21 1989-03-21 General Electric Company High strength superalloy for high temperature applications
US4830934A (en) * 1987-06-01 1989-05-16 General Electric Company Alloy powder mixture for treating alloys

Also Published As

Publication number Publication date
CH675256A5 (zh) 1990-09-14
AU3084989A (en) 1989-09-07
NO172812B (no) 1993-06-01
JP2825836B2 (ja) 1998-11-18
NO172812C (no) 1993-09-08
NO890874L (no) 1989-09-04
AU610996B2 (en) 1991-05-30
NO890874D0 (no) 1989-03-01
DE58901443D1 (de) 1992-06-25
EP0330858A1 (de) 1989-09-06
CA1334632C (en) 1995-03-07
US4957703A (en) 1990-09-18
JPH02149627A (ja) 1990-06-08

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