CN114045452A - Forging and heat treatment method of Haynes242 alloy forging - Google Patents
Forging and heat treatment method of Haynes242 alloy forging Download PDFInfo
- Publication number
- CN114045452A CN114045452A CN202111349475.8A CN202111349475A CN114045452A CN 114045452 A CN114045452 A CN 114045452A CN 202111349475 A CN202111349475 A CN 202111349475A CN 114045452 A CN114045452 A CN 114045452A
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- Prior art keywords
- forging
- haynes242
- heat treatment
- alloy
- temperature
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- 238000005242 forging Methods 0.000 title claims abstract description 61
- 239000000956 alloy Substances 0.000 title claims abstract description 49
- 229910045601 alloy Inorganic materials 0.000 title claims abstract description 49
- 238000010438 heat treatment Methods 0.000 title claims abstract description 45
- 238000000034 method Methods 0.000 title claims abstract description 25
- 230000032683 aging Effects 0.000 claims abstract description 16
- 238000005096 rolling process Methods 0.000 claims abstract description 5
- 238000004080 punching Methods 0.000 claims abstract description 4
- 239000000243 solution Substances 0.000 claims description 14
- 238000004321 preservation Methods 0.000 claims description 3
- 230000002045 lasting effect Effects 0.000 claims description 2
- 239000006104 solid solution Substances 0.000 claims description 2
- 239000000463 material Substances 0.000 description 5
- 238000012360 testing method Methods 0.000 description 5
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 description 3
- 238000007789 sealing Methods 0.000 description 3
- 238000004519 manufacturing process Methods 0.000 description 2
- 230000007547 defect Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000018109 developmental process Effects 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 229910052759 nickel Inorganic materials 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Classifications
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
- C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
- C22F1/10—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of nickel or cobalt or alloys based thereon
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21J—FORGING; HAMMERING; PRESSING METAL; RIVETING; FORGE FURNACES
- B21J5/00—Methods for forging, hammering, or pressing; Special equipment or accessories therefor
- B21J5/002—Hybrid process, e.g. forging following casting
Abstract
The invention belongs to the field of annular roll forming of aviation annular forged pieces, and particularly relates to a forging and heat treatment method of a Haynes242 alloy forged piece, which comprises the steps of upsetting, punching, trestle reaming and final rolling a Haynes242 alloy blank at the temperature of 1030 ℃ and 1120 ℃ to ensure that the deformation is 20-40% to obtain the Haynes242 alloy forged piece, and then sequentially carrying out solution heat treatment and aging heat treatment on the Haynes242 alloy forged piece; the Haynes242 alloy forging prepared by the method has the advantages of uniform grain structure, fine grain size, good high-temperature durability and good mechanical property.
Description
Technical Field
The invention belongs to the field of ring rolling forming of aviation annular forged pieces, and particularly relates to a forging and heat treatment method of a Haynes242 alloy forged piece.
Background
The Haynes242 alloy is an age-hardenable material that has excellent strength and ductility in aged condition and good workability in the annealed condition. The Haynes242 alloy has a higher yield strength than typical solution strengthened nickel-based alloys (e.g., HASTELLOYS alloy) and also has excellent ductility under full heat treatment. This can translate into excellent sealing characteristics of gas turbine rings and casings, particularly in combination with the low coefficient of expansion and excellent ductility after thermal expansion of the Haynes242 alloy. The Haynes242 alloy has excellent strength and ductility, and can be used as a low-temperature direct aging product. Coupled with its low thermal expansion characteristics, makes it an excellent choice for fasteners and springs.
Research shows that reasonable selection of forging temperature and heat treatment temperature can produce forgings with uniform structures and stable performance, ensure that all indexes of the forgings meet standard requirements, and meet normal use of parts.
However, the literature reports on the Haynes242 alloy as a novel aviation part material are few at present, and reference information which can be consulted is very little, so that the technical scheme of the Haynes242 alloy as the aviation part material can be realized only by continuous tests, and therefore, the forging and heat treatment method of the Haynes242 alloy needs to be researched.
Disclosure of Invention
The invention provides a forging and heat treatment method of a Haynes242 alloy forging aiming at the defects of the prior art.
The method is realized by the following technical scheme:
a forging and heat treatment method of a Haynes242 alloy forging comprises the following steps:
1) forging: upsetting, punching, trestle reaming and final rolling the Haynes242 alloy blank at the temperature of 1030 ℃ and 1120 ℃ to ensure that the deformation is 20-40%, and preserving heat to obtain a Haynes242 alloy forging;
2) solution heat treatment: carrying out solution heat treatment on the Haynes242 alloy forging at 1038-;
3) and (4) aging heat treatment.
More preferably, the forging temperature is 1030-.
Still more preferably, the forging temperature is 1030-1050 ℃.
In the step 1), the heat preservation time is equal to the effective thickness of the blank multiplied by 6min/10 mm.
The grain size of the Haynes242 alloy forging after solution heat treatment and aging heat treatment is more than or equal to grade 4.
Further, the solid solution temperature is either 1038 ℃, 1060 ℃ or 1080 ℃.
The aging heat treatment process conditions are as follows: the temperature is 649 ℃ and the time is 48 h.
The qualified value set by the tensile property parameters of the Haynes242 alloy forged piece subjected to aging heat treatment is as follows: the tensile strength is more than or equal to 127ksi, the yield strength is more than or equal to 70ksi, the elongation is more than or equal to 19 percent, and the reduction of area is more than or equal to 27 percent in a high-temperature stretching state at 649 ℃.
The smooth endurance performance parameter of the Haynes242 alloy forged piece subjected to aging heat treatment is set to have a qualified value as follows: the lasting time is more than or equal to 23 hours under the conditions of 649 ℃ and the loading strength of 95 ksi.
The Haynes242 alloy blank comprises the following chemical components in percentage by mass: 7-9% of Cr, 24-25% of Mo, less than or equal to 0.5% of Cu, less than or equal to 0.8% of Mn, less than or equal to 0.8% of Si, and less than or equal to 0.03% of C; p is less than or equal to 0.03 percent; less than or equal to 0.015 percent of S and less than or equal to 0.5 percent of Al; b is less than or equal to 0.006 percent; fe is less than or equal to 0.2 percent, and the balance is Ni.
The Haynes242 alloy forging prepared by the method is used for manufacturing a high-pressure turbine sealing ring, a high-pressure compressor rotor and a high-pressure compressor casing.
Has the advantages that:
(1) according to the forging and heat treatment method for the Haynes242 alloy forging, the Haynes242 alloy forging which is forged and subjected to heat treatment through the method is uniform in grain structure and fine in grain size, and provides material support for development of aviation parts, such as parts for manufacturing high-pressure turbine sealing rings, high-pressure compressor rotors, high-pressure compressor casings and the like.
(2) The Haynes242 alloy forged piece prepared by the method has good high-temperature durability and mechanical properties.
Detailed Description
The following is a detailed description of the embodiments of the present invention, but the present invention is not limited to these embodiments, and any modifications or substitutions in the basic spirit of the embodiments are included in the scope of the present invention as claimed in the claims.
Examples 1 to 5
A forging method of a Haynes242 alloy forging is characterized in that a Haynes242 alloy blank is subjected to upsetting, punching, saddle reaming and finish rolling under the heating temperature condition shown in table 1, the heat preservation time is equal to the effective thickness of the blank multiplied by 6min/10mm, the deformation of the blank is 30%, and the Haynes242 alloy forging is obtained, wherein the grain size of the forging is shown in table 1;
TABLE 1
Example 6
The Haynes242 alloy forgings forged in the examples 1 to 5 are subjected to solution heat treatment for 60min under the conditions shown in the table 2; the grain size is shown in table 2:
the results of Table 1 and Table 2 are combined to show that: the forging temperature is 1030 ℃ or 1050 ℃ and the heat treatment system is 1038 ℃ or 1060 ℃.
Example 7
Two samples were arbitrarily taken from each group of the Haynes242 alloy forgings forged in examples 1 to 5 and subjected to solution heat treatment at 1038 ℃, 1060 ℃, 1080 ℃ and 1093 ℃, all the samples were subjected to aging heat treatment at 649 ℃ for 48 hours, high-temperature stretching at 649 ℃ and a 649 ℃ durability test were performed after the aging, two samples were taken from each group for measurement, and the results are shown in Table 3:
TABLE 3
The results in Table 3 show that the forgings subjected to the solution heat treatment at 1038 ℃ and 1060 ℃ have the characteristics of high strength and poor plasticity; 1093 ℃ solution heat treated forgings have poor plasticity and low strength, and the forgings subjected to 1080 ℃ solution heat treatment under the same aging treatment condition have better performance.
The forging samples after solution heat treatment at 1080 ℃ for 60min and aging heat treatment at 649 ℃ for 48h are subjected to a high-temperature combination durability test at 649 ℃, and the results are shown in table 4:
TABLE 4649 ℃ high temperature smoothness durability test:
from the test results, the material durability of the forging obtained in example 2 after the solution heat treatment at 1080 ℃ for 60min and the aging heat treatment at 649 ℃ for 48h was the best.
Claims (9)
1. A forging and heat treatment method for a Haynes242 alloy forging is characterized by comprising the following steps:
1) forging: upsetting, punching, trestle reaming and final rolling the Haynes242 alloy blank at the temperature of 1030 ℃ and 1120 ℃ to ensure that the deformation is 20-40%, and preserving heat to obtain a Haynes242 alloy forging;
2) solution heat treatment: carrying out solution heat treatment on the Haynes242 alloy forging at 1038-;
3) and (4) aging heat treatment.
2. The method of claim 1 wherein the forging temperature is 1030-1070 ℃.
3. The method for forging and heat treating the Haynes242 alloy forging as recited in claim 1 or 2, wherein the forging temperature is 1030 ℃ and 1050 ℃.
4. The forging and heat treatment method of the Haynes242 alloy forging as claimed in claim 1, wherein in the step 1), the heat preservation time is the effective thickness of the blank multiplied by 6min/10 mm.
5. The forging and heat treatment method of the Haynes242 alloy forging as claimed in claim 1, wherein the grain size of the Haynes242 alloy forging after solution heat treatment and aging heat treatment is not less than 4 grade.
6. The forging and heat treatment method of the Haynes242 alloy forging as claimed in claim 1, wherein the solid solution temperature is any one of 1038 ℃, 1060 ℃ and 1080 ℃.
7. The forging and heat treatment method of the Haynes242 alloy forging as set forth in claim 1, wherein the aging heat treatment process conditions are as follows: the temperature is 649 ℃ and the time is 48 h.
8. The method for forging and thermally treating the Haynes242 alloy forging as claimed in claim 1, wherein the set qualified values of the tensile property parameters of the Haynes242 alloy forging subjected to aging heat treatment are as follows: the tensile strength is more than or equal to 127ksi, the yield strength is more than or equal to 70ksi, the elongation is more than or equal to 19 percent, and the reduction of area is more than or equal to 27 percent in a high-temperature stretching state at 649 ℃.
9. The forging and heat treatment method of the Haynes242 alloy forging as set forth in claim 1, wherein the smooth endurance performance parameter of the aged Haynes242 alloy forging is set to be a qualified value as follows: the lasting time is more than or equal to 23 hours under the conditions of 649 ℃ and the loading strength of 95 ksi.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111349475.8A CN114045452A (en) | 2021-11-15 | 2021-11-15 | Forging and heat treatment method of Haynes242 alloy forging |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111349475.8A CN114045452A (en) | 2021-11-15 | 2021-11-15 | Forging and heat treatment method of Haynes242 alloy forging |
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| CN114045452A true CN114045452A (en) | 2022-02-15 |
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| CN202111349475.8A Pending CN114045452A (en) | 2021-11-15 | 2021-11-15 | Forging and heat treatment method of Haynes242 alloy forging |
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Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1412331A (en) * | 2001-06-28 | 2003-04-23 | 海恩斯国际公司 | Two-step ageing treatment of Ni-Gr-Mo alloy |
| US20030084975A1 (en) * | 2001-06-28 | 2003-05-08 | Pike Lee M. | Aging treatment for Ni-Cr-Mo alloys |
| CN103189531A (en) * | 2011-02-18 | 2013-07-03 | 海恩斯国际公司 | High temperature low thermal expansion Ni-Mo-Cr alloy |
| CN112481565A (en) * | 2020-11-12 | 2021-03-12 | 贵州航宇科技发展股份有限公司 | Forging method of Waspaloy alloy |
-
2021
- 2021-11-15 CN CN202111349475.8A patent/CN114045452A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1412331A (en) * | 2001-06-28 | 2003-04-23 | 海恩斯国际公司 | Two-step ageing treatment of Ni-Gr-Mo alloy |
| US20030084975A1 (en) * | 2001-06-28 | 2003-05-08 | Pike Lee M. | Aging treatment for Ni-Cr-Mo alloys |
| CN103189531A (en) * | 2011-02-18 | 2013-07-03 | 海恩斯国际公司 | High temperature low thermal expansion Ni-Mo-Cr alloy |
| CN112481565A (en) * | 2020-11-12 | 2021-03-12 | 贵州航宇科技发展股份有限公司 | Forging method of Waspaloy alloy |
Non-Patent Citations (1)
| Title |
|---|
| 裴丙红等: "抗海洋环境腐蚀低膨胀高温合金GH242的研制", 《钢铁研究学报》 * |
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