EP0924309A2 - Nickelsuperlegierung mit Tantal - Google Patents
Nickelsuperlegierung mit Tantal Download PDFInfo
- Publication number
- EP0924309A2 EP0924309A2 EP98309980A EP98309980A EP0924309A2 EP 0924309 A2 EP0924309 A2 EP 0924309A2 EP 98309980 A EP98309980 A EP 98309980A EP 98309980 A EP98309980 A EP 98309980A EP 0924309 A2 EP0924309 A2 EP 0924309A2
- Authority
- EP
- European Patent Office
- Prior art keywords
- tantalum
- nickel
- alloys
- base superalloy
- essentially
- 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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Classifications
-
- 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%
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C1/00—Making non-ferrous alloys
- C22C1/04—Making non-ferrous alloys by powder metallurgy
- C22C1/0433—Nickel- or cobalt-based alloys
Definitions
- This invention is directed to nickel base superalloys and in particular to such alloys which contain tantalum and a ⁇ strengthening phase.
- ⁇ strengthened nickel base superalloys are extensively employed in high performance environment articles.
- the problems with such alloys relate to the high solvus temperature of the ⁇ phase. This temperature usually has a value very close to the incipient melting point of the alloy.
- Direct hot isostatic pressing of superalloy powder has been used to produce large components in a near-net shape in order to reduce material use and machining waste.
- current processing routes include blank die compaction followed by extrusion and Forging.
- the most undesirable time-dependent crack growth behavior occurs when a hold-time is imposed at peak stress during the cycle, i.e., when the maximum tensile stress is held constant for a period of time.
- a forged nickel-base superalloy article body having fatigue crack growth rates at elevated temperature essentially independent of frequency of cyclical stress applied thereto in which the alloy composition consists essentially of, in weight percent, about 14-22 cobalt 10-14 chromium 2-6 molybdenum 3-5 aluminum 3-5 titanium 0.5-6 tantalum 0-.6 zirconium 0.01-0.1 boron 0.03-0.1 carbon balance essentially nickel
- this invention is directed to ⁇ ' strengthened nickel base superalloy compositions which can be forged and heat treated to exhibit essentially time independent fatigue crack resistance in combination with high tensile and rupture strength properties.
- Articles can be manufactured from these alloys using conventional cast and wrought technology, but powder processing techniques are preferred.
- the alloys of this invention consist essentially of nickel, chromium, cobalt, molybdenum, aluminum, titanium, zirconium, tantalum and boron.
- the ⁇ ' precipitate phase is present in an amount ranging from about 40 to about 60 percent by volume. These alloys are free of the gamma double prime phase.
- the forged alloy has a grain structure that is predominantly equiaxed with the grain size being about ASTM 5-8 and exhibits fatigue crack growth rates that are substantially independent of the frequency of fatigue stress intensity with or without intermittent periods during which maximum tensile stress is held. This fatigue cracking resistance is demonstrated at temperatures in excess of 1200°F.
- compositional range, in weight percent, of the alloys included within the scope of this invention is set out in Table 1 below.
- cobalt 14-22 chromium 10-14 molybdenum 2-6 aluminum 3-5 titanium 3-5 tantalum 0.5-6 zirconium 0-.6 boron 0.01-0.1 carbon 0.03-0.1 nickel balance
- the alloy as embodied by the invention has an alloy composition consisting essentially of: 17.7-18.0 cobalt 11.8-12 chromium 3.9-4.0 molybdenum 3.9-4.0 aluminum 3.9-4.0 titanium 3.8-4.0 tantalum 0.17-0.3 zirconium about 0.03 carbon 0.01-0.04 boron balance essentially nickel.
- the alloy compositions are selected so as developed from about 40 to about 60 volume percent of the ⁇ ' precipitate phase. This volume fraction of the ⁇ ' precipitate has been found to provide the required degree of forgeability in the ingot.
- Standard superalloy melting procedures can be used to prepare the alloy in powder form.
- Vacuum induction melting, vacuum arc remelting or electroslag refining or remelting can be used to prepare ingots of the alloy compositions which are converted to powder by conventional atomization techniques followed by compaction and formation of the near net shape article.
- phase transition temperature of the alloy composition will depend upon obtaining accurate information on the phase transition temperature of the alloy composition.
- Several different methods are available for determining the phase transition temperature of the superalloy. Differential thermal analysis is one such method.
- a second method requires metallographic examination of the series of samples which are cold rolled to about 30% reduction and then heat treated at various temperatures around the expected phase transition temperature. Each of these methods is carried out on samples of the alloy.
- the ⁇ ' precipitate solvus of an alloy composition of this invention is frequently in the range of from about 1050 to about 1175°C.
- Figure 1a is a graphic representation of fatigue crack growth resistance for the alloys shown in Table 1 at 1200°F.
- Figure 1b is a graphic representation of fatigue crack growth resistance for the same alloys obtained at 1400°F.
- Figures 1a and 1b illustrate that the crack growth resistance advantage for the alloys in this invention over niobium containing alloys and other selected alloys. At 1200°F most alloys do not exhibit time dependent crack growth. However, at 1400°F many alloys exhibit faster crack growth with longer tensile hold times. The 1400°F crack growth rates for the alloys of this invention do not depend strongly on the hold time. Thus, the crack growth resistance of this class of alloys is superior to that of prior art alloys and other alloys with similar compositions containing niobium.
- Ingots consisting essentially of the following composition were prepared by a vacuum induction melting and casting procedure: cobalt 14-22 chromium 10-14 molybdenum 2-6 aluminum 3-5 titanium 3-5 tantalum 0.5-6 zirconium 0-.6 boron 0.01-0.1 carbon 0.03-0.1 nickel balance
- the alloy as embodied by the invention, has an alloy composition consisting essentially of: 17.7-18.0 cobalt 11.8-12 chromium 3.9-4.0 molybdenum 3.9-4.0 aluminum 3.9-4.0 titanium 3.8-4.0 tantalum 0.17-0.3 zirconium about 0.03 carbon 0.01-0.04 boron balance essentially nickel.
- the alloy as embodied by the invention, has an alloy composition consisting essentially of: 17.5-18.5 cobalt 11.5-12.5 chromium 3.7-4.3 molybdenum 3.8-4.2 aluminum 3.8-4.2 titanium 3.7-4.3 tantalum 0.2-0.3 zirconium 0.01-0.04 carbon 0.01-0.04 boron balance essentially nickel.
- a powder was prepared by melting ingots of the selected composition in an argon gas atmosphere and atomizing the liquid metal using argon gas for atomization. The powder was sieved to remove particles coarser than 150 mesh.
- the -150 mesh powder was transferred to consolidation cans for initial densification using a closed die compaction procedure at a temperature of about 150°F below the ⁇ ' solvus. This was followed by extrusion using a 7:1 extrusion reduction ratio at a temperature approximately 100°F below the ⁇ ' solvus to produce a fully dense extrusion.
- the extrusions were then solution treated or annealed at a temperature above the ⁇ ' solvus temperature in the range of about 2140°F to about 2160°F for about 1 hour.
- This solvus solution treatment completely dissolves the ⁇ ' phase and forms a well annealed structure.
- the solution treatment also recrystallizes and coarsens the fine grain billet structure and permits controlled reprecipitation of the ⁇ ' during subsequent heat treatment and processing.
- the solution treated extrusions were then rapidly cooled for the solution treatment temperature using a controlled quench.
- This quench is performed at a rate sufficient to develop a uniform distribution of ⁇ ' throughout the article.
- a controlled fan helium quench having a cooling rate of about 250°F per minute was used.
- the alloy was aged at a temperature of about 1500°F to 1550°F for about 4 hours.
- a preferred temperature range for this aging treatment is about 1515°F to about 1535°F. Aging promotes uniform distribution of additional ⁇ ' and is particularly suited for an alloy designed for operating service at temperatures of about 1500 °F.
- Solution treating can be carried out at any temperature above which the ⁇ ' phase dissolves in the gamma matrix and below the incipient melting temperature of the alloy.
- the particular temperature at which ⁇ ' first begins to dissolve in the matrix is referred to as the ⁇ solvus temperature.
- the temperature range between the ⁇ ' solvus temperature and the incipient melting temperature is generally referred to as the supersolvus temperature range. This temperature range will vary depending upon the composition of the superalloy.
- the alloys of this invention were solution treated in the range of about 1175°C to 1200°C for about 1 hour. This solution treatment was followed by an aging treatment at a temperature of about 700°C to about 800°C for about 4-12 hours.
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- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Manufacture Of Alloys Or Alloy Compounds (AREA)
- Powder Metallurgy (AREA)
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US99190097A | 1997-12-17 | 1997-12-17 | |
US991900 | 2001-11-23 |
Publications (2)
Publication Number | Publication Date |
---|---|
EP0924309A2 true EP0924309A2 (de) | 1999-06-23 |
EP0924309A3 EP0924309A3 (de) | 1999-09-08 |
Family
ID=25537700
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP98309980A Withdrawn EP0924309A3 (de) | 1997-12-17 | 1998-12-04 | Nickelsuperlegierung mit Tantal |
Country Status (1)
Country | Link |
---|---|
EP (1) | EP0924309A3 (de) |
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2009112380A1 (en) * | 2008-03-14 | 2009-09-17 | Siemens Aktiengesellschaft | Nickel base alloy and use of it, turbine blade or vane and gas turbine |
EP2256222A1 (de) * | 2009-05-29 | 2010-12-01 | General Electric Company | Nickelbasierte Superlegierungen und daraus geformte Komponenten |
CN101899595A (zh) * | 2009-05-29 | 2010-12-01 | 通用电气公司 | 镍基超合金及由其制成的构件 |
CN115821117A (zh) * | 2022-11-29 | 2023-03-21 | 江西宝顺昌特种合金制造有限公司 | 一种gh4141高温合金及其制备方法 |
Citations (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5662749A (en) * | 1995-06-07 | 1997-09-02 | General Electric Company | Supersolvus processing for tantalum-containing nickel base superalloys |
-
1998
- 1998-12-04 EP EP98309980A patent/EP0924309A3/de not_active Withdrawn
Patent Citations (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5662749A (en) * | 1995-06-07 | 1997-09-02 | General Electric Company | Supersolvus processing for tantalum-containing nickel base superalloys |
Cited By (18)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2009112380A1 (en) * | 2008-03-14 | 2009-09-17 | Siemens Aktiengesellschaft | Nickel base alloy and use of it, turbine blade or vane and gas turbine |
EP2103700A1 (de) * | 2008-03-14 | 2009-09-23 | Siemens Aktiengesellschaft | Legierung auf Nickelbasis und Verwendung, Turbinenblatt oder -schaufel und Gasturbine |
CN101970702B (zh) * | 2008-03-14 | 2012-11-28 | 西门子公司 | 镍基合金及其用途,涡轮机叶片或轮叶以及燃气涡轮机 |
US7993101B2 (en) | 2008-03-14 | 2011-08-09 | Siemens Aktiengesellschaft | Nickel base alloy and use of it, turbine blade or vane and gas turbine |
CN101899595A (zh) * | 2009-05-29 | 2010-12-01 | 通用电气公司 | 镍基超合金及由其制成的构件 |
US8992700B2 (en) | 2009-05-29 | 2015-03-31 | General Electric Company | Nickel-base superalloys and components formed thereof |
JP2010275636A (ja) * | 2009-05-29 | 2010-12-09 | General Electric Co <Ge> | ニッケル基超合金及びその部品 |
JP2010280986A (ja) * | 2009-05-29 | 2010-12-16 | General Electric Co <Ge> | ニッケル基超合金及びその部品 |
CN101899594A (zh) * | 2009-05-29 | 2010-12-01 | 通用电气公司 | 镍基超合金及由其制成的构件 |
EP2256222A1 (de) * | 2009-05-29 | 2010-12-01 | General Electric Company | Nickelbasierte Superlegierungen und daraus geformte Komponenten |
US8992699B2 (en) | 2009-05-29 | 2015-03-31 | General Electric Company | Nickel-base superalloys and components formed thereof |
EP2256223A1 (de) * | 2009-05-29 | 2010-12-01 | General Electric Company | Nickelbasierte Superlegierungen und daraus geformte Komponenten |
CN101899594B (zh) * | 2009-05-29 | 2015-06-24 | 通用电气公司 | 镍基超合金及由其制成的构件 |
CN101899595B (zh) * | 2009-05-29 | 2015-08-05 | 通用电气公司 | 镍基超合金及由其制成的构件 |
CN104946933A (zh) * | 2009-05-29 | 2015-09-30 | 通用电气公司 | 镍基超合金及由其制成的构件 |
US9518310B2 (en) | 2009-05-29 | 2016-12-13 | General Electric Company | Superalloys and components formed thereof |
CN115821117A (zh) * | 2022-11-29 | 2023-03-21 | 江西宝顺昌特种合金制造有限公司 | 一种gh4141高温合金及其制备方法 |
CN115821117B (zh) * | 2022-11-29 | 2023-09-29 | 江西宝顺昌特种合金制造有限公司 | 一种gh4141高温合金及其制备方法 |
Also Published As
Publication number | Publication date |
---|---|
EP0924309A3 (de) | 1999-09-08 |
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