CN115768911A - Heat resistant wrought nickel-base alloys and articles thereof - Google Patents
Heat resistant wrought nickel-base alloys and articles thereof Download PDFInfo
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- CN115768911A CN115768911A CN202180047552.6A CN202180047552A CN115768911A CN 115768911 A CN115768911 A CN 115768911A CN 202180047552 A CN202180047552 A CN 202180047552A CN 115768911 A CN115768911 A CN 115768911A
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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
- C22C19/056—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%
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- Engineering & Computer Science (AREA)
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- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Forging (AREA)
Abstract
The invention relates to the field of metallurgy. A heat-resistant nickel-based alloy is proposed, comprising in weight percent: 12.0 to 16.0 percent of cobalt, 9.0 to 12.0 percent of chromium, 4.0 to 6.0 percent of tungsten, 4.0 to 6.0 percent of molybdenum, 4.0 to 5.5 percent of aluminum, 2.0 to 3.5 percent of titanium, 0.5 to 2.5 percent of tantalum, 0.08 to 0.13 percent of carbon, 0.403 to 0.05 percent of magnesium, 0.002 to 0.05 percent of lanthanum, 0.003 to 0.03 percent of boron, 0.005 to 0.02 percent of cerium and/or neodymium (respectively) and the balance of nickel. In addition, a product made of the above heat-resistant nickel-based alloy is also proposed. The technical effect of the proposed invention is an improvement of the short and long term strength and plasticity of the alloy at temperatures up to 800 ℃.
Description
Technical Field
The present invention relates to metallurgy, i.e. hot forging nickel-base alloys. It can be used to manufacture parts for Gas Turbine Engines (GTEs) operating at temperatures up to 800 ℃.
Background
The main requirements for such materials are as follows: short and long term strength, operating temperature and high manufacturability.
From the prior art, EP 718-grade (GOST 5632-2014) hastelloy is known for use in the manufacture of compressor blades. The chemical components are as follows by weight percent:
carbon is not more than 0.1
Chromium 14.0-16.0
4.0-5.2 parts of molybdenum
Niobium 0.8-1.5
Tungsten 2.5-3.5
0.9-1.4 of aluminum
Titanium 1.9-2.4
Cerium is not more than 0.1
Boron is not more than 0.008
Zirconium is not more than 0.02
Nickel 43.0-47.0
The balance of iron and impurities.
The disadvantages of this alloy are the limitation of the working temperature (up to 650 ℃) and the low long-term strength at a temperature of 800 ℃ (245 MPa).
Iron-nickel based heat resistant alloys (RU 2074899, IPC 22C 30/00, C22C 19/03, published 3/10 1997) are known for the manufacture of compressor blades. The chemical components of the material are as follows by weight percent:
carbon 0.01-0.06
Chromium 15.5-18.5
2.8-3.5 parts of molybdenum
Niobium 5.1-5.9
Nickel 51.5-56.5
0.3-0.7 of aluminum
Titanium 0.6-1.1
Vanadium 0.2-0.7
Boron 0.004-0.01
Yttrium 0.02-0.6
The balance being iron.
The disadvantages of this alloy are the limitation of the working temperature (up to 650 ℃) and the low long-term strength at a temperature of 650 ℃ (710 MPa).
The closest analog is the hot forged nickel base alloy EP220 (GOST 23705-79), which is designed for manufacturing GTE and GTU blades by forming. The chemical components of the material are as follows by weight percent:
carbon is not more than 0.08
Chromium 9.0-12.0
Cobalt 14.0-16.0
5.0-8.0 parts of molybdenum
Tungsten 5.0-7.0
Aluminum 3.9-4.8
Titanium 2.2-2.9
Boron is not more than 0.02
Vanadium 0.2-0.8
The balance being nickel and impurities.
The alloy has mechanical properties that are not high enough for use in advanced GTEs, namely: the short-term strength and elongation at normal temperature were 1,150MPa and 15%, respectively, the short-term strength and elongation at 800 ℃ were 940MPa and 14%, respectively, and the long-term strength at 800 ℃ was 470MPa.
Disclosure of Invention
The technical problem is that of the low mechanical properties of the alloy, the solution of which is provided by implementing the proposed invention and cannot be achieved by using prototypes.
The technical purpose of the invention is to manufacture a heat-resistant forging nickel-based alloy with higher mechanical property.
The technical effect of the proposed invention is the improvement of the short and long term strength and plasticity of the alloy at temperatures up to 800 ℃.
In order to achieve the set technical effect, a heat-resistant nickel-based alloy is provided, which comprises the following components in percentage by weight:
cobalt 12.0-16.0
Chromium 9.0-12.0
Tungsten 4.0-6.0
4.0-6.0 parts of molybdenum
Aluminum 4.0-5.5
Titanium 2.0-3.5
Tantalum 0.5-2.5
Carbon 0.08-0.13
Magnesium 0.003-0.05
Lanthanum 0.002-0.05
Boron 0.003-0.03
0.005-0.02 each of cerium and/or neodymium
The balance being nickel.
Also provided is a product made of the above heat-resistant nickel-based alloy.
The proposed alloys are based on (Ni, co, cr) in various morphologies 3 Gamma prime phases of (Al, ti, ta, W) compounds and gamma solid solutions based on nickel and cobalt, meC type carbides also being present in the alloy.
12-16% by weight, ensures the plasticity of the alloy, which makes it possible to produce billets from the alloy by a strain method. The portion of the carbide phase that ensures additional alloy strengthening is increased due to the increased carbon content in the metal.
Alloying with a predetermined amount of tantalum while meeting a predetermined tungsten and molybdenum content improves the stability and mechanical properties of the alloy at high temperatures.
Tantalum is primarily present in the gamma 'and carbide phase compositions and enhances their high temperature stability, while tungsten and molybdenum are primarily distributed in gamma' solid solution and enhance their strength.
Magnesium, boron, lanthanum, cerium and/or neodymium are added during the smelting process to remove oxides from the melt and reduce the amount of harmful impurities, thereby improving mechanical properties (short and long term strength and plasticity over the entire operating temperature range).
The composite microalloying with lanthanum and neodymium helps to remove harmful impurities from grain boundaries and other internal surfaces of the material interface and helps to strengthen the implementation of the mechanism, i.e., the formation of Ni on grain boundaries and precipitation phases x An intermetallic phase of spherical morphology of P3 my. In contrast to the prototype, vanadium was not added as an alloying element to the proposed alloy, as it would reduce the anti-scaling/scale thermal resistance of the alloy at temperatures close to 800 ℃.
The maximum effect of improving the short-term and long-term strength of the alloy over the entire working temperature range is achieved with the stated contents and proportions of the constituents in the proposed nickel-base alloy.
Detailed Description
The initial electrode was melted in a vacuum induction furnace and subsequently vacuum arc remelted to produce ingots from the proposed alloys of various compositions and prototype alloys.
The chemical composition is given in table 1.
The production of bars from ingots of the proposed alloys of various compositions and prototype alloys was carried out in two stages: ingots were forged on a 1,600 ton press and billets in the form of rods were extruded on a Bliss press.
The obtained bar is cut into blanks, and the blanks are subjected to heat treatment. They were then used to produce cylindrical samples to determine the mechanical properties:
short term strength
Yield point
Relative elongation σ at 20 deg.C 20 And shrinkage ratio psi 20 Short term intensity
Relative elongation σ 800 And shrinkage ratio psi 800 Long term strength at 800 ℃ based on 100 hours
The mechanical properties were determined on a fracture and universal tester.
The test results are given in table 2.
The data in table 2 show that the proposed alloy outperforms the prototype alloy in terms of short and long term strength and plasticity (relative elongation and shrinkage) of the alloy at temperatures up to 800 ℃.
The use of the proposed hot forged nickel-base alloy allows the manufacture of GTEs with higher tactical and technical parameters, improving the reliability of the products and extending their service life.
Compositions of the alloys and prototype alloys set forth in Table 1
Mechanical properties of the alloys and prototype alloys set forth in Table 2
Claims (2)
1. A heat-resistant forging nickel-based alloy contains cobalt, chromium, tungsten, molybdenum, aluminum, titanium, carbon, boron and nickel, and is characterized in that tantalum, magnesium, lanthanum, cerium and/or neodymium are added, and the components are in the following weight percentage:
cobalt 12.0-16.0
Chromium 9.0-12.0
Tungsten 4.0-6.0
4.0-6.0 parts of molybdenum
Aluminum 4.0-5.5
Titanium 2.0-3.5
Tantalum 0.5-2.5
Carbon 0.08-0.13
Magnesium 0.003-0.05
Lanthanum 0.002-0.05
Boron 0.003-0.03
0.005-0.02 each of cerium and/or neodymium
The balance being nickel.
2. A product made of a heat-resistant nickel-based alloy, characterized in that it is made of an alloy according to claim 1.
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| RU2020118382A RU2737835C1 (en) | 2020-06-03 | 2020-06-03 | Nickel-based heat-resistant wrought alloy and article made from it |
| RU2020118382 | 2020-06-03 | ||
| PCT/RU2021/000237 WO2021246908A1 (en) | 2020-06-03 | 2021-06-02 | Nickel-based heat-resistant wrought alloy and article made from same |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN115768911A true CN115768911A (en) | 2023-03-07 |
Family
ID=73792519
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202180047552.6A Pending CN115768911A (en) | 2020-06-03 | 2021-06-02 | Heat resistant wrought nickel-base alloys and articles thereof |
Country Status (3)
| Country | Link |
|---|---|
| CN (1) | CN115768911A (en) |
| RU (1) | RU2737835C1 (en) |
| WO (1) | WO2021246908A1 (en) |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR1451347A (en) * | 1964-07-10 | 1966-01-07 | Alloys for use at high temperatures | |
| US3228095A (en) * | 1960-04-13 | 1966-01-11 | Rolls Royce | Method of making turbine blades |
| GB1087051A (en) * | 1963-04-26 | 1967-10-11 | Int Nickel Ltd | Nickel-chromium alloys |
| JP2004518811A (en) * | 2000-02-29 | 2004-06-24 | ゼネラル・エレクトリック・カンパニイ | Nickel-based superalloy and turbine component manufactured from the superalloy |
| JP2007105735A (en) * | 2005-10-11 | 2007-04-26 | Hitachi Ltd | Friction welding method |
| CN104946933A (en) * | 2009-05-29 | 2015-09-30 | 通用电气公司 | Nickel-base superalloys and components formed thereof |
| RU2571674C1 (en) * | 2014-10-07 | 2015-12-20 | Федеральное государственное унитарное предприятие "Всероссийский научно-исследовательский институт авиационных материалов" (ФГУП "ВИАМ") | Heat-resistant deformed alloy on base of nickel and item made of this alloy |
| JPWO2016158705A1 (en) * | 2015-03-30 | 2017-05-25 | 日立金属株式会社 | Method for producing Ni-base superalloy |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5938863A (en) * | 1996-12-17 | 1999-08-17 | United Technologies Corporation | Low cycle fatigue strength nickel base superalloys |
| RU2365657C1 (en) * | 2008-02-21 | 2009-08-27 | Федеральное государственное унитарное предприятие "Всероссийский научно-исследовательский институт авиационных материалов" (ФГУП "ВИАМ") | Heat-resistant nickel-base wrought alloy and article made from this alloy |
-
2020
- 2020-06-03 RU RU2020118382A patent/RU2737835C1/en active
-
2021
- 2021-06-02 WO PCT/RU2021/000237 patent/WO2021246908A1/en active Application Filing
- 2021-06-02 CN CN202180047552.6A patent/CN115768911A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3228095A (en) * | 1960-04-13 | 1966-01-11 | Rolls Royce | Method of making turbine blades |
| GB1087051A (en) * | 1963-04-26 | 1967-10-11 | Int Nickel Ltd | Nickel-chromium alloys |
| FR1451347A (en) * | 1964-07-10 | 1966-01-07 | Alloys for use at high temperatures | |
| JP2004518811A (en) * | 2000-02-29 | 2004-06-24 | ゼネラル・エレクトリック・カンパニイ | Nickel-based superalloy and turbine component manufactured from the superalloy |
| JP2007105735A (en) * | 2005-10-11 | 2007-04-26 | Hitachi Ltd | Friction welding method |
| CN104946933A (en) * | 2009-05-29 | 2015-09-30 | 通用电气公司 | Nickel-base superalloys and components formed thereof |
| RU2571674C1 (en) * | 2014-10-07 | 2015-12-20 | Федеральное государственное унитарное предприятие "Всероссийский научно-исследовательский институт авиационных материалов" (ФГУП "ВИАМ") | Heat-resistant deformed alloy on base of nickel and item made of this alloy |
| JPWO2016158705A1 (en) * | 2015-03-30 | 2017-05-25 | 日立金属株式会社 | Method for producing Ni-base superalloy |
Non-Patent Citations (1)
| Title |
|---|
| 陈诗荪: "《合金钢锻造》", 国防工业出版社, pages: 116 * |
Also Published As
| Publication number | Publication date |
|---|---|
| RU2737835C1 (en) | 2020-12-03 |
| WO2021246908A1 (en) | 2021-12-09 |
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