EP1359231B1 - Nickel-Basis-Superlegierung - Google Patents
Nickel-Basis-Superlegierung Download PDFInfo
- Publication number
- EP1359231B1 EP1359231B1 EP03100776A EP03100776A EP1359231B1 EP 1359231 B1 EP1359231 B1 EP 1359231B1 EP 03100776 A EP03100776 A EP 03100776A EP 03100776 A EP03100776 A EP 03100776A EP 1359231 B1 EP1359231 B1 EP 1359231B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- nickel
- alloy
- ppm
- components
- temperature
- 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
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Classifications
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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%
Definitions
- the invention relates to the field of materials technology. It concerns a nickel-base superalloy, in particular for the production of Single crystal components (SX alloy) or components with directed solidified structure (DS alloy), such as blades for Gas turbines.
- SX alloy Single crystal components
- DS alloy directed solidified structure
- the inventive alloy is also for Conventionally cast components can be used.
- Such nickel-base superalloys are known. Single-crystal components from these alloys have at high temperatures very good material resistance. 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 as found in US 4,643,782, EP 0 208 645 and US 5,270,123, are included solid solution strengthening alloying elements, for example Re, W, Mo, Co, Cr, and ⁇ '-phase-forming elements, such as Al, Ta, and Ti.
- the Content of high-melting alloying elements (W, Mo, Re) in the Basic matrix (austenitic ⁇ -phase) increases continuously with increase the stress temperature of the alloy.
- To contain z. B. usual Nickel-based superalloys for single crystals 6-8% W, up to 6% Re and up to 2% Mo (in% by weight).
- the in the above-mentioned publications alloys disclosed have high creep resistance, good LCF (Low cycle fatigue fatigue) and HCF (high fatigue fatigue) Load cycle number) properties as well as a high oxidation resistance.
- Another problem of the known nickel-base superalloys is that the castability of large components, eg. B. at Gas turbine blades with a length of more than 80 mm, to be desired leaves.
- the casting of a perfect, relatively large directionally solidified Single-crystal component of a nickel-base superalloy is extreme difficult because most of these components have errors, e.g. B. Kleinwinkelkornskynskyn, "Frecklen" (these are defects due to a Chain of rectified grains with a high content of eutectic), equiaxial scattering margins, microporosities u. a.
- Grain boundaries are areas of high local disorder of the crystal lattice since In these areas, the neighboring grains collide and thus one certain disorientation exists between the crystal lattices. ever the greater the disorientation, the greater the disorder, d. H. more greater is the number of dislocations in the grain boundaries that are necessary are, so that the two grains fit together.
- the aim of the invention is to avoid the disadvantages mentioned.
- a nickel-based superalloy which have improved castability and higher Oxidation resistance compared to known nickel-base superalloys having.
- this alloy z For example for large gas turbine single crystal components with a length of> 80 mm be suitable.
- the nickel-based superalloy according to the invention is characterized by the following chemical composition (data in% by weight): 7.7-8.3 Cr 5.0-5.25 Co 2.0-2.1 Mo 7.8-8.3 W 5.8-6.1 Ta 4.9-5.1 Al 1.3-1.4 Ti 0.11-0.15 Si 0.11-0.15 Hf 200-750 ppm C 50-400 ppm B
- the advantages of the invention are that the alloy is very good is pourable and over the previously known state of the art improved oxidation resistance at high temperatures.
- the alloy has the following composition: 7.7-8.3 Cr 5.0-5.25 Co 2.0-2.1 Mo 7.8-8.3 W 5.8-6.1 Ta 4.9-5.1 Al 1.3-1.4 Ti 0.11-0.15 Si 0.11-0.15 Hf 200-300 ppm C 50-100 ppm B
- This alloy is ideally suited for the production of large single-crystal components, For example, blades for gas turbines.
- Nickel-based superalloys having the chemical composition given in Table 1 were investigated (in% by weight): Chemical composition of the investigated alloys VL1 (CMSX-11B) VL2 (CMSX-6) VL3 (CMSX-2) VL4 (René N5) L1 Ni rest rest rest rest rest Cr 12.4 9.7 7.9 7.12 7.7 Co 5.7 5.0 4.6 7.4 5.1 Not a word 0.5 3.0 0.6 1.4 2.0 W 5.1 - 8.0 4.9 7.8 Ta 5.18 2.0 6.0 6.5 5.84 al 3:59 4.81 5:58 6:07 5.0 Ti 4.18 4.71 0.99 00:03 1.4 Hf 00:04 00:05 - 00:17 00:12 C - - - 00:02 B - - - - 0005 Si - - - - 00:12 Nb 0.1 - - - - re - - - 2.84 -
- Alloy L1 is a nickel base superalloy for single crystal components, their composition under the claim of present invention falls.
- the alloys VL1, VL2, VL3 and VL4 comparative alloys under the designations CMSX-11B, CMSX-6, CMSX-2 and René N5 known prior art are. They differ, inter alia. from the alloy according to the invention all in that they are not alloyed with C, B and Si.
- FIGS. 1 to 5 a quasi-isothermal oxidation diagram is shown in each case for the comparative alloys VL1 to VL4 (FIGS. 1 to 4) and the alloy L1 according to the invention (FIG. 5).
- the specific mass change ⁇ m / A data in mg / cm 2 ) at temperatures of 800 ° C., 950 ° C., 1050 ° C. and 1100 ° C. in the range from 0 to 1000 h is shown for the alloys mentioned. Comparing the curves, the superiority of the alloy according to the invention is particularly evident in the case of the high temperatures (1000 ° C.) and the long removal times.
- nickel-base superalloys with higher C and B contents (max. 750 ppm C and max. 400 ppm B) selected according to claim 1 of the invention.
- the components produced from it can also be conventional to water.
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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)
- Crystals, And After-Treatments Of Crystals (AREA)
- Manufacture And Refinement Of Metals (AREA)
- Organic Low-Molecular-Weight Compounds And Preparation Thereof (AREA)
- Battery Electrode And Active Subsutance (AREA)
- Golf Clubs (AREA)
- Conductive Materials (AREA)
Description
7.7-8.3 Cr |
5.0-5.25 Co |
2.0-2.1 Mo |
7.8-8.3 W |
5.8-6.1 Ta |
4.9-5.1 Al |
1.3-1.4 Ti |
0.11-0.15 Si |
0.11-0.15 Hf |
200-750 ppm C |
50-400 ppm B |
7.7-8.3 Cr |
5.0-5.25 Co |
2.0-2.1 Mo |
7.8-8.3 W |
5.8-6.1 Ta |
4.9-5.1 Al |
1.3-1.4 Ti |
0.11-0.15 Si |
0.11-0.15 Hf |
200-300 ppm C |
50-100 ppm B |
- Fig. 1
- die Abhängigkeit der spezifischen Massenänderung von der Temperatur und Zeit für die Vergleichslegierung VL1;
- Fig. 2
- die Abhängigkeit der spezifischen Massenänderung von der Temperatur und Zeit für die Vergleichslegierung VL2;
- Fig. 3
- die Abhängigkeit der spezifischen Massenänderung von der Temperatur und Zeit für die Vergleichslegierung VL3;
- Fig. 4
- die Abhängigkeit der spezifischen Massenänderung von der Temperatur und Zeit für die Vergleichslegierung VL4 und
- Fig. 5
- die Abhängigkeit der spezifischen Massenänderung von der Temperatur und Zeit für die erfindungsgemässe Legierung L1.
Chemische Zusammensetzung der untersuchten Legierungen | |||||
VL1 (CMSX-11B) | VL2 (CMSX-6) | VL3 (CMSX-2) | VL4 (René N5) | L1 | |
Ni | Rest | Rest | Rest | Rest | Rest |
Cr | 12.4 | 9.7 | 7.9 | 7.12 | 7.7 |
Co | 5.7 | 5.0 | 4.6 | 7.4 | 5.1 |
Mo | 0.5 | 3.0 | 0.6 | 1.4 | 2.0 |
W | 5.1 | - | 8.0 | 4.9 | 7.8 |
Ta | 5.18 | 2.0 | 6.0 | 6.5 | 5.84 |
Al | 3.59 | 4.81 | 5.58 | 6.07 | 5.0 |
Ti | 4.18 | 4.71 | 0.99 | 0.03 | 1.4 |
Hf | 0.04 | 0.05 | - | 0.17 | 0.12 |
C | - | - | - | - | 0.02 |
B | - | - | - | - | 0.005 |
Si | - | - | - | - | 0.12 |
Nb | 0.1 | - | - | - | - |
Re | - | - | - | 2.84 | - |
Claims (3)
- Nickel-Basis-Superlegierung gekennzeichnet durch folgende chemische Zusammensetzung (Angaben in Gew.- %):
7.7-8.3 Cr 5.0-5.25 Co 2.0-2.1 Mo 7.8-8.3 W 5.8-6.1 Ta 4.9-5.1 Al 1.3-1.4 Ti 0.11-0.15 Si 0.11-0.15 Hf 200-750 ppm C 50-400 ppm B - Nickel-Basis-Superlegierung nach Anspruch 1, insbesondere zur Herstellung von Einkristall-Komponenten, gekennzeichnet durch folgende chemische Zusammensetzung (Angaben in Gew.- %):
7.7-8.3 Cr 5.0-5.25 Co 2.0-2.1 Mo 7.8-8.3 W 5.8-6.1 Ta 4.9-5.1 Al 1.3-1.4 Ti 0.11-0.15 Si 0.11-0.15 Hf 200-300 ppm C 50-100 ppm B - Nickel-Basis-Superlegierung nach Anspruch 2 gekennzeichnet durch folgende chemische Zusammensetzung (Angaben in Gew.- %):
7.7 Cr 5.1 Co 2.0 Mo 7.8 W 5.8 Ta 5.0 Al 1.4 Ti 0.12 Si 0.12 Hf 200 ppm C 50 ppm B
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CH00745/02A CH695497A5 (de) | 2002-04-30 | 2002-04-30 | Nickel-Basis-Superlegierung. |
CH7452002 | 2002-04-30 |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1359231A1 EP1359231A1 (de) | 2003-11-05 |
EP1359231B1 true EP1359231B1 (de) | 2005-10-19 |
Family
ID=28796666
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP03100776A Expired - Fee Related EP1359231B1 (de) | 2002-04-30 | 2003-03-26 | Nickel-Basis-Superlegierung |
Country Status (7)
Country | Link |
---|---|
US (1) | US6740292B2 (de) |
EP (1) | EP1359231B1 (de) |
JP (1) | JP4326830B2 (de) |
AT (1) | ATE307219T1 (de) |
CH (1) | CH695497A5 (de) |
DE (1) | DE50301388D1 (de) |
ES (1) | ES2250826T3 (de) |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102009032144A1 (de) | 2008-07-25 | 2010-01-28 | Alstom Technology Ltd. | Schutzrohre für Thermoelemente |
EP2354261A1 (de) | 2010-02-05 | 2011-08-10 | Alstom Technology Ltd | Nickel-Basis Superlegierung mit verbessertem Degradationsverhalten |
RU2525952C2 (ru) * | 2009-07-09 | 2014-08-20 | Альстом Текнолоджи Лтд. | Жаропрочный сплав на основе никеля |
Families Citing this family (14)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CA2586974C (en) * | 2004-11-18 | 2013-06-25 | Alstom Technology Ltd | Nickel-base superalloy |
SE528807C2 (sv) * | 2004-12-23 | 2007-02-20 | Siemens Ag | Komponent av en superlegering innehållande palladium för användning i en högtemperaturomgivning samt användning av palladium för motstånd mot väteförsprödning |
US20060182649A1 (en) * | 2005-02-16 | 2006-08-17 | Siemens Westinghouse Power Corp. | High strength oxidation resistant superalloy with enhanced coating compatibility |
US20060219329A1 (en) * | 2005-03-29 | 2006-10-05 | Honeywell International, Inc. | Repair nickel-based superalloy and methods for refurbishment of gas turbine components |
EP1900839B1 (de) * | 2006-09-07 | 2013-11-06 | Alstom Technology Ltd | Verfahren zur Wärmebehandlung von Nickel-Basis-Superlegierungen |
JP5439822B2 (ja) * | 2009-01-15 | 2014-03-12 | 独立行政法人物質・材料研究機構 | Ni基単結晶超合金 |
US20100254822A1 (en) * | 2009-03-24 | 2010-10-07 | Brian Thomas Hazel | Super oxidation and cyclic damage resistant nickel-base superalloy and articles formed therefrom |
US20110076179A1 (en) * | 2009-03-24 | 2011-03-31 | O'hara Kevin Swayne | Super oxidation and cyclic damage resistant nickel-base superalloy and articles formed therefrom |
US8449262B2 (en) * | 2009-12-08 | 2013-05-28 | Honeywell International Inc. | Nickel-based superalloys, turbine blades, and methods of improving or repairing turbine engine components |
WO2013167513A1 (en) | 2012-05-07 | 2013-11-14 | Alstom Technology Ltd | Method for manufacturing of components made of single crystal (sx) or directionally solidified (ds) superalloys |
US20160214350A1 (en) | 2012-08-20 | 2016-07-28 | Pratt & Whitney Canada Corp. | Oxidation-Resistant Coated Superalloy |
JP6267890B2 (ja) * | 2013-08-07 | 2018-01-24 | 三菱日立パワーシステムズ株式会社 | Ni基鋳造超合金および該Ni基鋳造超合金からなる鋳造物 |
EP2949768B1 (de) * | 2014-05-28 | 2019-07-17 | Ansaldo Energia IP UK Limited | Ausscheidungsgehärteten gamma-prime-superlegierung auf nickelbasis zur verwendung in verfahren zur herstellung pulverbasierter additive |
GB201615496D0 (en) | 2016-09-13 | 2016-10-26 | Rolls Royce Plc | Nickel-based superalloy and use thereof |
Family Cites Families (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4461659A (en) * | 1980-01-17 | 1984-07-24 | Cannon-Muskegon Corporation | High ductility nickel alloy directional casting of parts for high temperature and stress operation |
CA1212020A (en) * | 1981-09-14 | 1986-09-30 | David N. Duhl | Minor element additions to single crystals for improved oxidation resistance |
FR2557598B1 (fr) * | 1983-12-29 | 1986-11-28 | Armines | Alliage monocristallin a matrice a base de nickel |
US4643782A (en) | 1984-03-19 | 1987-02-17 | Cannon Muskegon Corporation | Single crystal alloy technology |
US4885216A (en) * | 1987-04-03 | 1989-12-05 | Avco Corporation | High strength nickel base single crystal alloys |
US4677035A (en) * | 1984-12-06 | 1987-06-30 | Avco Corp. | High strength nickel base single crystal alloys |
US4719080A (en) | 1985-06-10 | 1988-01-12 | United Technologies Corporation | Advanced high strength single crystal superalloy compositions |
GB2234521B (en) * | 1986-03-27 | 1991-05-01 | Gen Electric | Nickel-base superalloys for producing single crystal articles having improved tolerance to low angle grain boundaries |
US5435861A (en) * | 1992-02-05 | 1995-07-25 | Office National D'etudes Et De Recherches Aerospatiales | Nickel-based monocrystalline superalloy with improved oxidation resistance and method of production |
US5270123A (en) | 1992-03-05 | 1993-12-14 | General Electric Company | Nickel-base superalloy and article with high temperature strength and improved stability |
EP0789087B1 (de) * | 1996-02-09 | 2000-05-10 | Hitachi, Ltd. | Hochfeste Superlegierung auf Nickelbasis für gerichtet erstarrte Giesteilen |
-
2002
- 2002-04-30 CH CH00745/02A patent/CH695497A5/de not_active IP Right Cessation
-
2003
- 2003-03-26 ES ES03100776T patent/ES2250826T3/es not_active Expired - Lifetime
- 2003-03-26 DE DE50301388T patent/DE50301388D1/de not_active Expired - Lifetime
- 2003-03-26 AT AT03100776T patent/ATE307219T1/de active
- 2003-03-26 EP EP03100776A patent/EP1359231B1/de not_active Expired - Fee Related
- 2003-03-28 US US10/400,415 patent/US6740292B2/en not_active Expired - Lifetime
- 2003-04-23 JP JP2003118858A patent/JP4326830B2/ja not_active Expired - Fee Related
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102009032144A1 (de) | 2008-07-25 | 2010-01-28 | Alstom Technology Ltd. | Schutzrohre für Thermoelemente |
RU2525952C2 (ru) * | 2009-07-09 | 2014-08-20 | Альстом Текнолоджи Лтд. | Жаропрочный сплав на основе никеля |
EP2354261A1 (de) | 2010-02-05 | 2011-08-10 | Alstom Technology Ltd | Nickel-Basis Superlegierung mit verbessertem Degradationsverhalten |
US8696980B2 (en) | 2010-02-05 | 2014-04-15 | Alstom Technology Ltd | Nickel-base superalloy with improved degradation behavior |
Also Published As
Publication number | Publication date |
---|---|
DE50301388D1 (de) | 2006-03-02 |
ATE307219T1 (de) | 2005-11-15 |
CH695497A5 (de) | 2006-06-15 |
JP4326830B2 (ja) | 2009-09-09 |
US20040005238A1 (en) | 2004-01-08 |
JP2004027361A (ja) | 2004-01-29 |
ES2250826T3 (es) | 2006-04-16 |
US6740292B2 (en) | 2004-05-25 |
EP1359231A1 (de) | 2003-11-05 |
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