EP1420075A1 - Superalliage à base de nickel - Google Patents

Superalliage à base de nickel Download PDF

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Publication number
EP1420075A1
EP1420075A1 EP03104108A EP03104108A EP1420075A1 EP 1420075 A1 EP1420075 A1 EP 1420075A1 EP 03104108 A EP03104108 A EP 03104108A EP 03104108 A EP03104108 A EP 03104108A EP 1420075 A1 EP1420075 A1 EP 1420075A1
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.)
Granted
Application number
EP03104108A
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German (de)
English (en)
Other versions
EP1420075B1 (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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    • 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 affects a nickel-based superalloy, especially for the production of Single crystal components, such as blades for gas turbines.
  • Such nickel-based superalloys are known. Single-crystal components of these alloys exhibit a high temperature very good material strength. This can, for. B. the inlet temperature of Gas turbines are increased, which increases the efficiency of the gas turbine.
  • Nickel-based superalloys for single crystal components such as those from US 4,643,782, EP 0 208 645 and US 5,270,123 are known mixed crystal strengthening alloy elements, for example Re, W, Mo, Co, Cr, and ⁇ '-phase-forming elements, for example Al, Ta, and Ti. Der Content of high melting alloy elements (W, Mo, Re) in the Basic matrix (austenitic ⁇ phase) increases continuously with the increase the stress temperature of the alloy. So contain z. B. usual Nickel-based superalloys for single crystals 6-8% W, up to 6% Re and up 2% Mo (figures in% by weight). The in the above mentioned publications Alloys disclosed have high creep resistance, good LCF (Fatigue with low number of load cycles) - and HCF (fatigue with high Number of load cycles) properties and a high oxidation resistance.
  • the alloys known, for example, from US Pat. No. 5,270,123 also have comparable disadvantages.
  • This lattice distortion prevents dislocations when sliding or cutting the ⁇ 'grains.
  • the lattice distortion causes an increase in the short-term strength, but with prolonged stress, the structure becomes coarser and then a degradation of the ⁇ 'structure and thus a long-term mechanical weakening of the alloy.
  • This disadvantage is overcome with the alloy known from EP 0 914 483 B1 eliminated.
  • This nickel-based 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, where the ratio of (Ta + 1.5 Hf + 0.5 Mo - 0.5 Ti) / (W + 1.2 Re) ⁇ 0.7 is.
  • these alloys Due to the ratio mentioned, these alloys have the Alloy elements at operating temperature no lattice offset between the ⁇ -phase and the ⁇ '-phase, which ensures high long-term stability moderate load is reached. It also has rhenium alloyed nickel-based superalloy excellent castability and great phase stability combined with the best mechanical Characteristics. 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 object of the invention is to provide a nickel-based superalloy develop which on the one hand has a solid and strong ⁇ phase as a matrix and which on the other hand only a small proportion, i.e. less than 50%, has ⁇ '-phase, and is therefore very resistant to oxidation and a exhibits good creep behavior.
  • the advantages of the invention are that the alloy is a good one Has degradation behavior.
  • the ⁇ phase (matrix) is determined by the Alloying of ruthenium solidifies, despite the absence of Rhenium, which according to the known prior art is particularly good Mixed crystal strengthener applies and therefore the properties of the ⁇ matrix strongly improved.
  • the alloy according to the invention is characterized by good ones Creep rupture strength, stable structure and good castability.
  • the oxidation resistance of the alloy is very good. she is excellently suited for the production of single crystal components, for example, blades for gas turbines.
  • Nickel-based superalloys with the chemical composition given in Table 1 were examined (data in% by weight): Chemical composition of the alloys examined L1 (AMN1) L2 (AMN3) VL (PW 1483) Ni rest rest rest Cr 9.96 12:34 12.8 Co 8.86 8.84 9 Mo 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 is below the claims of the present invention fall.
  • the alloy VL is a comparison alloy, which is called PW 1483 is known prior art. It differs from the Alloys according to the invention especially in that they are not Ruthenium is alloyed and there is no significant Si content.
  • the alloys L2 and VL are almost identical. This applies to the Cr content also towards the alloy L1. With L1 the Cr content is approx. 3% by weight less than with the comparison alloy VL.
  • the Vickers hardness HV2 was measured. The results listed in Table 2 were achieved. Vickers hardness for the alloys examined L1 VL HV2 447 403
  • the alloy L1 thus has a hardness that is more than 10% higher than that Comparative alloy VL.
  • the ⁇ phase (matrix) of the Alloys are mainly solidified by the alloyed ruthenium.
  • FIG. 1 shows the structure of the comparative alloy VL1
  • FIG. 2 shows that Structure of the alloy L1 according to the invention shows.
  • alloy L1 is clearly the lower Proportion of ⁇ '-phase (dark particles) can be seen.
  • the ⁇ 'phase (secondary, intermetallic phase formed by precipitation hardening) has in the Alloy VL has an approximately square shape and is strip-shaped in the matrix arranged.
  • the ⁇ 'phase in L1 has a spherical shape, what an indication of a very slight lattice offset between the ⁇ and the ⁇ 'phase represents.
  • This slight lattice offset and, above all, the small one Volume fraction of ⁇ '-phase (less than 50%) have an effect on this positive that there is no ⁇ / ⁇ 'inversion of the microstructure, i.e. the ⁇ '-phase is embedded in the ⁇ -phase and does not form a continuous network.
  • a good degradation behavior of the inventive Alloys 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 stretched.

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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)
EP03104108A 2002-11-12 2003-11-06 Superalliage à base de nickel Expired - Lifetime 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 true EP1420075A1 (fr) 2004-05-19
EP1420075B1 EP1420075B1 (fr) 2006-02-22

Family

ID=31946562

Family Applications (1)

Application Number Title Priority Date Filing Date
EP03104108A Expired - Lifetime 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)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2145968A1 (fr) * 2008-07-14 2010-01-20 Siemens Aktiengesellschaft Superalliage renforcé d'amorce de gamme à base de nickel

Families Citing this family (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CA2586974C (fr) * 2004-11-18 2013-06-25 Alstom Technology Ltd Superalliage a base de nickel
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
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
GB2587635B (en) * 2019-10-02 2022-11-02 Alloyed Ltd A Nickel-based alloy

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4719080A (en) * 1985-06-10 1988-01-12 United Technologies Corporation Advanced high strength single crystal superalloy compositions
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

Family Cites Families (7)

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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
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
DE50006694D1 (de) * 1999-07-29 2004-07-08 Siemens Ag Hochtemperaturbeständiges bauteil und verfahren zur herstellung des hochtemperaturbeständigen bauteils
US6468367B1 (en) * 1999-12-27 2002-10-22 General Electric Company Superalloy weld composition and repaired turbine engine component

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4719080A (en) * 1985-06-10 1988-01-12 United Technologies Corporation Advanced high strength single crystal superalloy compositions
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

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
PATENT ABSTRACTS OF JAPAN vol. 1999, no. 03 31 March 1999 (1999-03-31) *

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2145968A1 (fr) * 2008-07-14 2010-01-20 Siemens Aktiengesellschaft Superalliage renforcé d'amorce de gamme à base de nickel
WO2010006974A1 (fr) * 2008-07-14 2010-01-21 Siemens Aktiengesellschaft Superalliage à base de nickel renforcé par une phase gamma prime
RU2450067C1 (ru) * 2008-07-14 2012-05-10 Сименс Акциенгезелльшафт Суперсплав на никелевой основе с упрочняющей гамма-штрих-фазой
CN102089449B (zh) * 2008-07-14 2012-09-05 西门子公司 镍基γ'相强化的超合金
US8431073B2 (en) 2008-07-14 2013-04-30 Siemens Aktiengesellschaft Nickel base gamma prime strengthened superalloy

Also Published As

Publication number Publication date
JP4523264B2 (ja) 2010-08-11
US6706241B1 (en) 2004-03-16
JP2004285472A (ja) 2004-10-14
DE50302468D1 (de) 2006-04-27
EP1420075B1 (fr) 2006-02-22

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