EP1420075B1 - Superalliage à base de nickel - Google Patents

Superalliage à base de nickel Download PDF

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Publication number
EP1420075B1
EP1420075B1 EP03104108A EP03104108A EP1420075B1 EP 1420075 B1 EP1420075 B1 EP 1420075B1 EP 03104108 A EP03104108 A EP 03104108A EP 03104108 A EP03104108 A EP 03104108A EP 1420075 B1 EP1420075 B1 EP 1420075B1
Authority
EP
European Patent Office
Prior art keywords
ppm
nickel
alloy
phase
alloys
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.)
Expired - Fee Related
Application number
EP03104108A
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German (de)
English (en)
Other versions
EP1420075A1 (fr
Inventor
Robert Baumann
David Duhl
Andreas KÜNZLER
Mohamed Yousef Nazmy
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
General Electric Technology GmbH
Original Assignee
Alstom Technology AG
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Publication date
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Application filed by Alstom Technology AG filed Critical Alstom Technology AG
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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 invention relates to the field of materials technology. It relates to a nickel-base superalloy, in particular for the production of single-crystal components, such as blades for gas turbines.
  • Such nickel-base superalloys are known. Single crystal components of these alloys have a very good material strength at high temperatures. As a result, z. B. the inlet temperature of gas turbines are increased, whereby the efficiency of the gas turbine increases.
  • Nickel-based superalloys for single-crystal components contain mixed-crystal-hardening alloying elements, for example Re, W, Mo, Co, Cr, and ⁇ '-phase-forming elements, for example, Al, Ta, and Ti.
  • the content of refractory alloying elements (W, Mo, Re) in the base matrix (austenitic ⁇ -phase) continuously increases with the increase of the stress temperature of the Alloy.
  • refractory alloying elements (W, Mo, Re) in the base matrix continuously increases with the increase of the stress temperature of the Alloy.
  • the alloys disclosed in the above references have high creep strength, good LCF (low duty cycle fatigue) and HCF (high cycle fatigue) properties, and high oxidation resistance.
  • the alloys known from US 5,270,123 have comparable disadvantages.
  • a positive or a negative lattice offset between the matrix forming ⁇ phase and the ⁇ 'phase, ie the secondary intermetallic phase Ni 3 Al, in the case of the Ta, Ti, Hf partial Al and Co, and Cr can partly replace Ni.
  • This lattice distortion hinders dislocations when sliding or cutting the ⁇ '-grains.
  • the lattice distortion causes an increase in the Kurrzeitfestmaschine, but with prolonged stress, a coarsening of the microstructure and then a degradation of the ⁇ 'structure and thus causes a long-term mechanical weakening of the alloy.
  • This disadvantage is eliminated with the alloy known from EP 0 914 483 B1.
  • This nickel base superalloy consists essentially of (measured in% by weight) 6.0-6.8% Cr, 8.0-10.0% Co, 0.5-0.7% Mo, 6.2-6.6% W, 2.7-3.2% Re, 5.4- 5.8% Al, 0.5-0.9% Ti, 7.2-7.8% Ta, 0.15-0.3% Hf, 0.02-0.04% C, 40-100 ppm B, 0-400 ppm Y, balance Ni with impurities, the ratio of ( Ta + 1.5 Hf + 0.5 Mo - 0.5 Ti) / (W + 1.2 Re) ⁇ 0.7.
  • this nickel-base superalloy alloyed with rhenium has excellent castability and high phase stability combined with the best mechanical properties. It is also characterized by high fatigue strength and creep stability even with long-term exposure.
  • the aim of the invention is to avoid the disadvantages mentioned.
  • the invention is based on the object to develop a nickel-based superalloy, which on the one hand has a strong and strong ⁇ -phase as a matrix and which on the other hand only a small proportion, i. less than 50%, at ⁇ '-phase, and thus is very resistant to oxidation and has a good creep behavior.
  • the advantages of the invention are that the alloy has a good degradation behavior.
  • the ⁇ phase (matrix) is solidified by the addition of ruthenium, despite the absence of rhenium, which according to the known state of the art is considered to be a particularly good solid solution promoter and therefore greatly improves the properties of the ⁇ matrix.
  • the alloy according to the invention is distinguished by good creep rupture strength, stable microstructures and good castability.
  • the oxidation resistance of the alloy is very good. It is outstandingly suitable for the production of single-crystal components, for example blades for gas turbines.
  • the degradation behavior of the alloy according to the invention is good. There is no single crystal crack growth and no large decrease in yield strength at room temperature in the degraded state compared to the non-degraded state.
  • Nickel-based superalloys having the chemical composition given in Table 1 were investigated (in% by weight): Table 1: Chemical composition of the investigated alloys L1 (AMN1) L2 (AMN3) VL (PW 1483) Ni rest rest rest Cr 9.96 12:34 12.8 Co 8.86 8.84 9 Not a word 1:47 1.85 1.9 W 3:45 3.76 3.8 Ta 4 4.96 4 al 3:57 3:45 3.8 Ti 3.83 3.96 4 Hf 0.5 00:48 - C 0025 0033 - B 86 ppm 79 ppm - Si 10 ppm 10 ppm - Ru 1:07 00:28 -
  • Alloys L1 and L2 are alloys whose composition falls within the claims of the present invention.
  • alloy VL is a comparative alloy known in the art as PW 1483. It differs from the alloys according to the invention primarily in that it is not alloyed with ruthenium and no appreciable Si content is present.
  • the alloys L2 and VL are almost identical. This is true up to the Cr content on the alloy L1. In the case of L1, the Cr content is about 3% by weight lower than in the case of the comparative alloy VL.
  • the alloy L1 thus has over 10% higher hardness than the comparative alloy VL.
  • the ⁇ -phase (matrix) of the alloys according to the invention is solidified mainly by the alloyed ruthenium.
  • FIG. 1 shows the microstructure of the comparative alloy VL1
  • FIG. 2 shows the microstructure of the alloy L1 according to the invention.
  • the smaller proportion of ⁇ '-phase (dark particles) is clearly recognizable in the alloy L1.
  • the ⁇ '-phase secondary precipitation-hardening intermetallic phase
  • the ⁇ '-phase in L1 has a spherical shape, which is an indication of a very small lattice offset between the ⁇ and the ⁇ 'phase.
  • This small lattice offset and, above all, the low volume fraction of ⁇ '-phase (less than 50%) have a positive effect in that there is no ⁇ / ⁇ '-inversion of the microstructure, i. the ⁇ '-phase is embedded in the ⁇ -phase and does not form a continuous network.
  • a good degradation behavior of the inventive alloys is achieved.
  • the ⁇ '-phase is embedded in the ⁇ -phase and does not form a continuous network.
  • the alloy L1AD shows predominantly round to oval forms of the ⁇ '-phase, while in the alloy L2AD the ⁇ '-phase is very elongated.
  • Fig. 5 the weight change as a function of time for the three alloys is shown. After being degraded, the alloys according to the invention have a significantly lower weight change than the comparative alloy known from the prior art, ie they have a significantly better oxidation 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)

Claims (4)

  1. Superalliage à base de nickel prévu pour fabriquer des composants monocristallins, caractérisé par la composition chimique suivante (données en % en poids) :
    7-13 Cr
    4-10 Co
    0,5-2 Mo
    2-8 W
    4-6 Ta
    3-6 Al
    1-4 Ti
    0,1-6 Ru
    0,01-0,5 Hf
    0,001-0,15 Si
    0-700 ppm C
    0-300 ppm B

    le reste étant constitué de nickel et d'impuretés qui découlent de la fabrication.
  2. Superalliage à base de nickel selon la revendication 1, caractérisé par la composition chimique suivante (données en % en poids) :
    10-13 Cr
    8-9 Co
    1,5-2 Mo
    3-5 W
    4-5 Ta
    3-5 Al
    2-4 Ti
    0,3-4 Ru
    0,01-0,5 Hf
    0,001-0,15 Si
    0-700 ppm C
    0-300 ppm B

    le reste étant constitué de nickel et d'impuretés qui découlent de la fabrication.
  3. Superalliage à base de nickel selon la revendication 2, caractérisé par la composition chimique suivante (données en % en poids) :
    10-13 Cr
    8-9 Co
    1,5-2 Mo
    3,5-4 W
    4-5 Ta
    3,5-5 Al
    3-4 Ti
    0,3-1,5 Ru
    0,5 Hf
    10-500 ppm Si
    250-350 ppm C
    80-100 ppm B

    le reste étant constitué de nickel et d'impuretés qui découlent de la fabrication.
  4. Superalliage à base de nickel selon la revendication 1, caractérisé par la composition chimique suivante (données en % en poids) :
    7-9 Cr
    8-9 Co
    1,5-2 Mo
    3-5 W
    5-6 Ta
    3-5 Al
    1-2 Ti
    0,5-1,5 Ru
    0,5 Hf
    700 ppm C
    100 ppm B
    500 ppm Si

    le reste étant constitué de nickel et d'impuretés qui découlent de la fabrication.
EP03104108A 2002-11-12 2003-11-06 Superalliage à base de nickel Expired - Fee Related EP1420075B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US291392P 2002-11-12
US10/291,392 US6706241B1 (en) 2002-11-12 2002-11-12 Nickel-base superalloy

Publications (2)

Publication Number Publication Date
EP1420075A1 EP1420075A1 (fr) 2004-05-19
EP1420075B1 true EP1420075B1 (fr) 2006-02-22

Family

ID=31946562

Family Applications (1)

Application Number Title Priority Date Filing Date
EP03104108A Expired - Fee Related EP1420075B1 (fr) 2002-11-12 2003-11-06 Superalliage à base de nickel

Country Status (4)

Country Link
US (1) US6706241B1 (fr)
EP (1) EP1420075B1 (fr)
JP (1) JP4523264B2 (fr)
DE (1) DE50302468D1 (fr)

Families Citing this family (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN101061244B (zh) * 2004-11-18 2012-05-30 阿尔斯托姆科技有限公司 镍基高温合金
US20060182649A1 (en) * 2005-02-16 2006-08-17 Siemens Westinghouse Power Corp. High strength oxidation resistant superalloy with enhanced coating compatibility
US20100008790A1 (en) * 2005-03-30 2010-01-14 United Technologies Corporation Superalloy compositions, articles, and methods of manufacture
US8920937B2 (en) * 2007-08-05 2014-12-30 United Technologies Corporation Zirconium modified protective coating
US20130230405A1 (en) * 2007-08-31 2013-09-05 Kevin Swayne O'Hara Nickel base superalloy compositions being substantially free of rhenium and superalloy articles
US8876989B2 (en) 2007-08-31 2014-11-04 General Electric Company Low rhenium nickel base superalloy compositions and superalloy articles
EP2145968A1 (fr) * 2008-07-14 2010-01-20 Siemens Aktiengesellschaft Superalliage renforcé d'amorce de gamme à base de nickel
US8216509B2 (en) * 2009-02-05 2012-07-10 Honeywell International Inc. Nickel-base superalloys
US20110076180A1 (en) * 2009-09-30 2011-03-31 General Electric Company Nickel-Based Superalloys and Articles
US8708659B2 (en) * 2010-09-24 2014-04-29 United Technologies Corporation Turbine engine component having protective coating
US9752215B2 (en) 2012-02-14 2017-09-05 United Technologies Corporation Superalloy compositions, articles, and methods of manufacture
US9783873B2 (en) 2012-02-14 2017-10-10 United Technologies Corporation Superalloy compositions, articles, and methods of manufacture
US20160214350A1 (en) 2012-08-20 2016-07-28 Pratt & Whitney Canada Corp. Oxidation-Resistant Coated Superalloy

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1520630A (en) * 1974-07-08 1978-08-09 Johnson Matthey Co Ltd Platinum group metal-containing alloys
US4643782A (en) 1984-03-19 1987-02-17 Cannon Muskegon Corporation Single crystal alloy technology
US4719080A (en) * 1985-06-10 1988-01-12 United Technologies Corporation Advanced high strength single crystal superalloy compositions
CA1315572C (fr) * 1986-05-13 1993-04-06 Xuan Nguyen-Dinh Materiaux monocristallins a phase stable
US5270123A (en) 1992-03-05 1993-12-14 General Electric Company Nickel-base superalloy and article with high temperature strength and improved stability
DE19624055A1 (de) 1996-06-17 1997-12-18 Abb Research Ltd Nickel-Basis-Superlegierung
JPH10330872A (ja) * 1997-05-29 1998-12-15 Toshiba Corp Ｎｉ基耐熱超合金及びＮｉ基耐熱超合金部品
EP1204776B1 (fr) * 1999-07-29 2004-06-02 Siemens Aktiengesellschaft Piece resistant a des temperatures elevees et son procede de production
US6468367B1 (en) * 1999-12-27 2002-10-22 General Electric Company Superalloy weld composition and repaired turbine engine component

Also Published As

Publication number Publication date
EP1420075A1 (fr) 2004-05-19
DE50302468D1 (de) 2006-04-27
JP2004285472A (ja) 2004-10-14
US6706241B1 (en) 2004-03-16
JP4523264B2 (ja) 2010-08-11

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