CN105970129A - Low-stress manufacturing process for eliminating anisotropism of 2A12 aluminum alloy forging - Google Patents
Low-stress manufacturing process for eliminating anisotropism of 2A12 aluminum alloy forging Download PDFInfo
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- CN105970129A CN105970129A CN201610522430.9A CN201610522430A CN105970129A CN 105970129 A CN105970129 A CN 105970129A CN 201610522430 A CN201610522430 A CN 201610522430A CN 105970129 A CN105970129 A CN 105970129A
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- product
- aluminum alloy
- manufacturing process
- stress
- anisotropism
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- 229910000838 Al alloy Inorganic materials 0.000 title claims abstract description 27
- 238000005242 forging Methods 0.000 title claims abstract description 16
- 238000004519 manufacturing process Methods 0.000 title claims abstract description 15
- 238000000034 method Methods 0.000 claims abstract description 25
- 238000010791 quenching Methods 0.000 claims abstract description 12
- 230000000171 quenching effect Effects 0.000 claims abstract description 8
- 238000010438 heat treatment Methods 0.000 claims abstract description 4
- 230000035882 stress Effects 0.000 claims description 17
- 238000001816 cooling Methods 0.000 claims description 6
- 230000032683 aging Effects 0.000 claims description 5
- 230000001351 cycling effect Effects 0.000 claims description 5
- 239000002994 raw material Substances 0.000 claims description 3
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 2
- 238000003754 machining Methods 0.000 abstract description 14
- 239000000463 material Substances 0.000 abstract description 8
- 239000002699 waste material Substances 0.000 abstract description 2
- 239000007769 metal material Substances 0.000 abstract 1
- 238000005496 tempering Methods 0.000 abstract 1
- 230000008030 elimination Effects 0.000 description 5
- 238000003379 elimination reaction Methods 0.000 description 5
- 238000005516 engineering process Methods 0.000 description 5
- 239000000956 alloy Substances 0.000 description 4
- 229910045601 alloy Inorganic materials 0.000 description 2
- 230000006835 compression Effects 0.000 description 2
- 238000007906 compression Methods 0.000 description 2
- -1 Aero-Space Chemical compound 0.000 description 1
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 229910052782 aluminium Inorganic materials 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- PCHJSUWPFVWCPO-UHFFFAOYSA-N gold Chemical compound [Au] PCHJSUWPFVWCPO-UHFFFAOYSA-N 0.000 description 1
- 239000010931 gold Substances 0.000 description 1
- 229910052737 gold Inorganic materials 0.000 description 1
- 238000002360 preparation method 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
- C22F1/04—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon
- C22F1/057—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon of alloys with copper as the next major constituent
-
- 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
- C22F1/002—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working by rapid cooling or quenching; cooling agents used therefor
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- Chemical & Material Sciences (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Crystallography & Structural Chemistry (AREA)
- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Forging (AREA)
Abstract
The invention relates to a low-stress manufacturing process for eliminating anisotropism of a 2A12 aluminum alloy forging, and belongs to the field of metal material engineering. In the aerospace field, according to the use and stress environment of an aluminum alloy product, the requirement for lowering the anisotropism of a material is high, and especially the requirements of an airtight knuckle bearing type forging for the chordwise and radial strength and toughness of the product are higher. Especially the requirement of an airtight knuckle bearing for a space suit for the machining precision of the product is quite high. For an aluminum alloy capable of being subjected to heat treatment and strengthening, after the material is quenched, large internal quenching stress exists in the material, and for the product with the high requirement for machining precision, waste can be possibly caused by size tolerance after finish machining. According to the method, the anisotropism, in the chordwise direction and the radial direction, of the product can be effectively eliminated, especially the internal stress of the product is effectively eliminated, and the machining yield of the product is remarkably increased.
Description
Technical field
The present invention relates to a kind of elimination 2A12 aluminum alloy forge piece anisotropic low stress manufacturing process, belong to gold
Belong to material engineering field, use this method can effectively eliminate each to different in tangential and radial direction of product
Property, particularly effectively eliminate the internal stress of product, significantly improve the machining yield rate of product.
Background technology
In aerospace field, according to use and the force environment of alloy product, to reducing each of material
Anisotropy requires higher, the most airtight oscillating bearing forging, to the tangential of product and intensity radially and
Toughness reguirements is higher.Particularly the airtight oscillating bearing of space flight spacesuit, non-to the requirement on machining accuracy of product
Chang Gao.
Mostly traditional manufacture method is to use extruded bars and extruding tubing directly to process, and so processes
The airtight oscillating bearing arrived is more excellent in tangential performance, but also requires that higher radial direction in stress
Can be relatively low, the particularly percentage elongation of material is relatively low, there is potential safety hazard during life-time service.
It addition, for the aluminium alloy of heat-treatable strengthened class, at material after quenching, material is deposited
In bigger quenching internal stress, for the product that requirement on machining accuracy is high, after polish it is possible to
Waste product is caused because of dimension overproof.
Summary of the invention
It is an object of the invention to: the invention provides a kind of eliminate 2A12 aluminum alloy forge piece anisotropic low should
Power manufacturing process, utilizes the airtight oscillating bearing forging that this technique produces in tangential and radial direction anisotropy
Inconspicuous, effectively eliminate the internal stress of product, significantly improve the machining yield rate of product.
The technical scheme is that a kind of anisotropic low stress of 2A12 aluminum alloy forge piece that eliminates manufactures work
Skill, this technique comprises following step:
(1) the aluminium alloy extruded bar selecting raw material to be the 2A12-O1 state meeting GJB3539；
(2) the flat-die forging technique using two upsettings one to pull out prepares the 2A12 aluminium alloy forging of the size of required product
Part；
(3) quenching 2A12 aluminum alloy forge piece, quench system: 490～505 DEG C/2～6h, room temperature water
Quench, carry out the precommpression deformation of 1-5%；
(4) artificial aging, combines cold cycling technique in ag(e)ing process.
In described step (2), blank heating system: 380～420 DEG C/3～6h；Mould heating-up temperature is
380～420 DEG C.
Technological parameter in described step (4) is :-100 DEG C～-120 DEG C/10min～30min, 160 DEG C～190 DEG C
/ 0.5h～4h, air cooling ,-100 DEG C～-120 DEG C/10min～30min, 160 DEG C～190 DEG C/0.5h～4h, air cooling.
This technique is the production of aluminum alloy forge piece in Aeronautics and Astronautics, boats and ships and automobile.
The invention has the beneficial effects as follows:
1) use 2A12 extruded bar stock to carry out repeatedly upsetting pull deformation process, effectively reduce extruding formation and knit
The impact of structure, eliminates in tangential and radial direction anisotropy, and can increase the deflection of aluminum alloy materials,
Enhance product performance.
2) employing carries out cold compression after quenching, and combines cold cycling elimination stress work in artificial aging process
Skill, has not only saved the cycle produced and cost, has the most effectively eliminated the internal stress of product, the machine of product
Machining deformation amount is reduced to ± 50 μm by original ± 200 μm, and machining yield rate is more than 98%.
Accompanying drawing explanation
Fig. 1 is the TEM photo of 2A12 alloy forged piece in the present invention.
Detailed description of the invention
A kind of elimination 2A12 aluminum alloy forge piece anisotropic low stress manufacturing process, specifically comprises following step
Rapid:
(1) raw material is the aluminium alloy extruded bar of the Ф 150mm2A12-O1 state meeting GJB3539；
(2) the flat-die forging technique using two upsettings one to pull out prepares the 2A12 aluminium alloy forging of the size of required product
Part, specifically comprises the processes of: blank heating system: 380～420 DEG C/3～6h；Mould heating-up temperature is 380～420 DEG C；
Billet size is Ф 150mm × 505mm, and Forging Technology is: the first upsetting is to 200mm, and first pulls out commutation pulls out
Long to Ф 200mm, the second upsetting to 135mm；
(3) the quenching system of 2A12 aluminum alloy forge piece: 490～505 DEG C/2～6h, room temperature shrend, is carried out immediately
The precommpression deformation of 1-5%.
(4) combining cold cycling technique during artificial aging to carry out, concrete technology parameter is :-100 DEG C
～-120 DEG C/10min～30min, 160 DEG C～190 DEG C/0.5h～4h, air cooling ,-100 DEG C～-120 DEG C
/ 10min～30min, 160 DEG C～190 DEG C/0.5h～4h, air cooling.
Table 1 gives the 2A12 aluminum alloy forge piece prepared according to new technology proposed by the invention and traditional handicraft
Illustration is implemented at tangential and tensile property radially.It is found that forging prepared by present invention process is at two
Performance on direction is close, and almost without anisotropy, and the more tangential difference of the radial performance of traditional handicraft is very
Many, particularly percentage elongation is the lowest.
Table 1 present invention and traditional handicraft prepare the performance comparison of forging
Table 2 gives the 2A12 aluminum alloy forge piece prepared according to new technology proposed by the invention and traditional handicraft
Machinability implement illustration.It is found that the internal stress of forging prepared by present invention process is little, machine adds
Work deflection only has ± 50 μm, can meet the use requirement of product completely, machines the more traditional work of yield rate
Skill improves a lot.
Table 2 present invention and traditional handicraft prepare the machinability of forging
| Preparation method | Machining distortion amount | Machining yield rate |
| The present invention | ±50μm | 98% |
| Traditional handicraft | ±200μm | 15% |
In sum, a kind of elimination 2A12 aluminum alloy forge piece anisotropic low stress manufacture of the present invention
Technique, effectively reduces extruding and forms the impact of texture, eliminates properties of product tangential each with radial direction
Anisotropy.Carry out cold compression after quenching it addition, use, and combine cold cycling in artificial aging process and disappear
De-stress technique, has effectively eliminated the internal stress of product, reduces machining deformation, being machined to of product
Product rate significantly improves.This technique may extend to the aluminum alloy materials of other heat-treatable strengthened classes, the most right
Multiple directions performance and machining distortion require high product, relate to the aluminum such as Aero-Space, boats and ships and automobile and close
The production of bodkin part, has bigger market potential.
Claims (4)
1. one kind eliminates 2A12 aluminum alloy forge piece anisotropic low stress manufacturing process, it is characterised in that:
This technique comprises following step:
(1) the aluminium alloy extruded bar selecting raw material to be the 2A12-O1 state meeting GJB3539；
(2) the flat-die forging technique using two upsettings one to pull out prepares the 2A12 aluminium alloy forging of the size of required product
Part；
(3) quenching 2A12 aluminum alloy forge piece, quench system: 490～505 DEG C/2～6h, room temperature water
Quench, carry out the precommpression deformation of 1-5%；
(4) artificial aging, combines cold cycling technique in ag(e)ing process.
Low stress manufacturing process the most according to claim 1, it is characterised in that: described step (2)
In, blank heating system: 380～420 DEG C/3～6h；Mould heating-up temperature is 380～420 DEG C.
Low stress manufacturing process the most according to claim 1, it is characterised in that: described step (4)
In technological parameter be :-100 DEG C～-120 DEG C/10min～30min, 160 DEG C～190 DEG C/0.5h～4h, air cooling,
-100 DEG C～-120 DEG C/10min～30min, 160 DEG C～190 DEG C/0.5h～4h, air cooling.
Low stress manufacturing process the most according to claim 1, it is characterised in that: this technique for aviation,
The production of aluminum alloy forge piece in space flight, boats and ships and automobile.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610522430.9A CN105970129B (en) | 2016-07-05 | 2016-07-05 | One kind eliminates the anisotropic low stress manufacturing process of 2A12 aluminum alloy forge pieces |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610522430.9A CN105970129B (en) | 2016-07-05 | 2016-07-05 | One kind eliminates the anisotropic low stress manufacturing process of 2A12 aluminum alloy forge pieces |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105970129A true CN105970129A (en) | 2016-09-28 |
| CN105970129B CN105970129B (en) | 2017-09-29 |
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|---|---|---|---|
| CN201610522430.9A Active CN105970129B (en) | 2016-07-05 | 2016-07-05 | One kind eliminates the anisotropic low stress manufacturing process of 2A12 aluminum alloy forge pieces |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110791721A (en) * | 2019-11-28 | 2020-02-14 | 西南铝业（集团）有限责任公司 | Quenching method of 2014 aluminum alloy aviation precision hub die forging |
| CN111822634A (en) * | 2020-05-26 | 2020-10-27 | 洛阳中重铸锻有限责任公司 | Shape control method for improving homogeneity of die steel |
| CN113088649A (en) * | 2021-03-30 | 2021-07-09 | 贵州航天电子科技有限公司 | Heat treatment method for bracket and bracket processing technology using heat treatment method |
| CN115584450A (en) * | 2022-08-30 | 2023-01-10 | 河南北方红阳机电有限公司 | 2A12 aluminum alloy graded annealing heat treatment process |
Citations (5)
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|---|---|---|---|---|
| CN101649433A (en) * | 2009-07-10 | 2010-02-17 | 西南铝业（集团）有限责任公司 | Method for processing aluminum alloy plates |
| CN102676959A (en) * | 2012-05-29 | 2012-09-19 | 苏州市新鸿基精密部品有限公司 | Aluminum alloy high and low temperature stress relief aging method |
| CN103131970A (en) * | 2011-11-22 | 2013-06-05 | 贵州航天乌江机电设备有限责任公司 | Aluminium alloy aging treatment method |
| CN104357776A (en) * | 2014-10-24 | 2015-02-18 | 陈帆 | Processing method of 2014 aluminum alloy plate |
| CN104372270A (en) * | 2014-10-24 | 2015-02-25 | 陈帆 | Processing method of 2A12 aluminum alloy plate |
-
2016
- 2016-07-05 CN CN201610522430.9A patent/CN105970129B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101649433A (en) * | 2009-07-10 | 2010-02-17 | 西南铝业（集团）有限责任公司 | Method for processing aluminum alloy plates |
| CN103131970A (en) * | 2011-11-22 | 2013-06-05 | 贵州航天乌江机电设备有限责任公司 | Aluminium alloy aging treatment method |
| CN102676959A (en) * | 2012-05-29 | 2012-09-19 | 苏州市新鸿基精密部品有限公司 | Aluminum alloy high and low temperature stress relief aging method |
| CN104357776A (en) * | 2014-10-24 | 2015-02-18 | 陈帆 | Processing method of 2014 aluminum alloy plate |
| CN104372270A (en) * | 2014-10-24 | 2015-02-25 | 陈帆 | Processing method of 2A12 aluminum alloy plate |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110791721A (en) * | 2019-11-28 | 2020-02-14 | 西南铝业（集团）有限责任公司 | Quenching method of 2014 aluminum alloy aviation precision hub die forging |
| CN111822634A (en) * | 2020-05-26 | 2020-10-27 | 洛阳中重铸锻有限责任公司 | Shape control method for improving homogeneity of die steel |
| CN111822634B (en) * | 2020-05-26 | 2022-08-16 | 洛阳中重铸锻有限责任公司 | Shape control method for improving homogeneity of die steel |
| CN113088649A (en) * | 2021-03-30 | 2021-07-09 | 贵州航天电子科技有限公司 | Heat treatment method for bracket and bracket processing technology using heat treatment method |
| CN115584450A (en) * | 2022-08-30 | 2023-01-10 | 河南北方红阳机电有限公司 | 2A12 aluminum alloy graded annealing heat treatment process |
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| Publication number | Publication date |
|---|---|
| CN105970129B (en) | 2017-09-29 |
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