EP1420075A1 - Nickel-Basis-Superlegierung - Google Patents
Nickel-Basis-Superlegierung Download PDFInfo
- 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.)
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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)
Abstract
Description
- Fig. 1
- ein Gefügebild der Vergleichslegierung VL;
- Fig. 2
- ein Gefügebild der erfindungsgemässen Legierung L1;
- Fig. 3
- ein Gefügebild der erfindungsgemässen Legierung L1 nach Degradierung;
- Fig. 4
- ein Gefügebild der erfindungsgemässen Legierung L2 nach Degradierung;
- Fig. 5
- ein Diagramm, welches die Gewichtsänderung der Legierungen VL, L1 und L2 in Abhängigkeit von der Zeit angibt;
- Fig. 6
- ein Diagramm, welches die 0,2%-Streckgrenze der Legierungen VL, L1 und L2 in Abhängigkeit vom Degradations-Parameter angibt und
- Fig. 7
- ein Diagramm, welches die Spannung (1%-Dehngrenze) der Legierungen VL, L1 und L2 in Abhängigkeit vom Larson Miller-Parameter angibt.
Chemische Zusammensetzung der untersuchten Legierungen | |||
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 | 0.48 | - |
C | 0.025 | 0.033 | - |
B | 86 ppm | 79 ppm | - |
Si | 10 ppm | 10 ppm | - |
Ru | 1.07 | 0.28 | - |
Vickers-Härte für die untersuchten Legierungen | ||
L1 | VL | |
HV2 | 447 | 403 |
Claims (4)
- Nickel-Basis-Superlegierung zur Herstellung von Einkristall-Komponenten gekennzeichnet durch folgende chemische Zusammensetzung (Angaben in Gew.-%):7-13 Cr4-10 Co0.5-2 Mo2-8 W4-6 Ta3-6 Al1-4 Ti0.1-6 Ru0.01-0.5 Hf0.001-0.15 Si0-700 ppm C0-300 ppm B
- Nickel-Basis-Superlegierung nach Anspruch 1, gekennzeichnet durch folgende chemische Zusammensetzung (Angaben in Gew.-%):10-13 Cr8-9 Co1.5-2 Mo3-5 W4-5 Ta3-5 Al2-4 Ti0.3-4 Ru0.01-0.5 Hf0.001-0.15 Si0-700 ppm C0-300 ppm B
- Nickel-Basis-Superlegierung nach Anspruch 2, gekennzeichnet durch folgende chemische Zusammensetzung (Angaben in Gew.-%):10-13 Cr8-9 Co1.5-2 Mo3.5-4 W4-5 Ta3.5-5 Al3-4 Ti0.3-1.5 Ru0.5 Hf10-500 ppm Si250-350 ppm C80-100 ppm B
- Nickel-Basis-Superlegierung nach Anspruch 1, gekennzeichnet durch folgende chemische Zusammensetzung (Angaben in Gew.-%),7-9 Cr8-9 Co1.5-2 Mo3-5 W5-6 Ta3-5 Al1-2 Ti0.5-1.5 Ru0.5 Hf500 ppm Si700 ppm C100 ppm B
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 (de) | 2004-05-19 |
EP1420075B1 EP1420075B1 (de) | 2006-02-22 |
Family
ID=31946562
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP03104108A Expired - Fee Related EP1420075B1 (de) | 2002-11-12 | 2003-11-06 | Nickel-Basis-Superlegierung |
Country Status (4)
Country | Link |
---|---|
US (1) | US6706241B1 (de) |
EP (1) | EP1420075B1 (de) |
JP (1) | JP4523264B2 (de) |
DE (1) | DE50302468D1 (de) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2145968A1 (de) * | 2008-07-14 | 2010-01-20 | Siemens Aktiengesellschaft | Gamma-Strich-verstärkte Superlegierung auf Nickelbasis |
Families Citing this family (13)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP5186215B2 (ja) * | 2004-11-18 | 2013-04-17 | アルストム テクノロジー リミテッド | ニッケルベース超合金 |
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 |
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 |
US9783873B2 (en) | 2012-02-14 | 2017-10-10 | United Technologies Corporation | Superalloy compositions, articles, and methods of manufacture |
US9752215B2 (en) | 2012-02-14 | 2017-09-05 | 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)
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)
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 (en) * | 1986-05-13 | 1993-04-06 | Xuan Nguyen-Dinh | Phase stable single crystal materials |
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 |
EP1204776B1 (de) * | 1999-07-29 | 2004-06-02 | Siemens Aktiengesellschaft | 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 |
-
2002
- 2002-11-12 US US10/291,392 patent/US6706241B1/en not_active Expired - Lifetime
-
2003
- 2003-11-06 DE DE50302468T patent/DE50302468D1/de not_active Expired - Lifetime
- 2003-11-06 EP EP03104108A patent/EP1420075B1/de not_active Expired - Fee Related
- 2003-11-12 JP JP2003383045A patent/JP4523264B2/ja not_active Expired - Fee Related
Patent Citations (2)
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)
Title |
---|
PATENT ABSTRACTS OF JAPAN vol. 1999, no. 03 31 March 1999 (1999-03-31) * |
Cited By (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2145968A1 (de) * | 2008-07-14 | 2010-01-20 | Siemens Aktiengesellschaft | Gamma-Strich-verstärkte Superlegierung auf Nickelbasis |
WO2010006974A1 (en) * | 2008-07-14 | 2010-01-21 | Siemens Aktiengesellschaft | Nickel base gamma prime strengthened superalloy |
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 |
EP1420075B1 (de) | 2006-02-22 |
DE50302468D1 (de) | 2006-04-27 |
US6706241B1 (en) | 2004-03-16 |
JP2004285472A (ja) | 2004-10-14 |
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