CN109423586B - Aging process for improving texture and performance of 7N01 aluminum alloy - Google Patents
Aging process for improving texture and performance of 7N01 aluminum alloy Download PDFInfo
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- 229910000838 Al alloy Inorganic materials 0.000 title claims abstract description 69
- 230000032683 aging Effects 0.000 title claims abstract description 52
- 230000035882 stress Effects 0.000 claims abstract description 27
- 238000000034 method Methods 0.000 claims abstract description 14
- VYZAMTAEIAYCRO-UHFFFAOYSA-N Chromium Chemical compound [Cr] VYZAMTAEIAYCRO-UHFFFAOYSA-N 0.000 claims abstract description 4
- FYYHWMGAXLPEAU-UHFFFAOYSA-N Magnesium Chemical compound [Mg] FYYHWMGAXLPEAU-UHFFFAOYSA-N 0.000 claims abstract description 4
- PWHULOQIROXLJO-UHFFFAOYSA-N Manganese Chemical compound [Mn] PWHULOQIROXLJO-UHFFFAOYSA-N 0.000 claims abstract description 4
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 claims abstract description 4
- QCWXUUIWCKQGHC-UHFFFAOYSA-N Zirconium Chemical compound [Zr] QCWXUUIWCKQGHC-UHFFFAOYSA-N 0.000 claims abstract description 4
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims abstract description 4
- 229910052782 aluminium Inorganic materials 0.000 claims abstract description 4
- 229910052804 chromium Inorganic materials 0.000 claims abstract description 4
- 239000011651 chromium Substances 0.000 claims abstract description 4
- 239000012535 impurity Substances 0.000 claims abstract description 4
- 239000011777 magnesium Substances 0.000 claims abstract description 4
- 229910052749 magnesium Inorganic materials 0.000 claims abstract description 4
- 229910052748 manganese Inorganic materials 0.000 claims abstract description 4
- 239000011572 manganese Substances 0.000 claims abstract description 4
- 239000010936 titanium Substances 0.000 claims abstract description 4
- 229910052719 titanium Inorganic materials 0.000 claims abstract description 4
- 229910052726 zirconium Inorganic materials 0.000 claims abstract description 4
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 claims abstract description 3
- 229910052802 copper Inorganic materials 0.000 claims abstract description 3
- 239000010949 copper Substances 0.000 claims abstract description 3
- 229910052720 vanadium Inorganic materials 0.000 claims abstract description 3
- LEONUFNNVUYDNQ-UHFFFAOYSA-N vanadium atom Chemical compound [V] LEONUFNNVUYDNQ-UHFFFAOYSA-N 0.000 claims abstract description 3
- 239000013078 crystal Substances 0.000 claims description 13
- 238000001125 extrusion Methods 0.000 claims description 7
- 238000009826 distribution Methods 0.000 claims description 4
- 238000005096 rolling process Methods 0.000 claims description 2
- 239000000203 mixture Substances 0.000 claims 1
- 230000008569 process Effects 0.000 abstract description 11
- 238000001556 precipitation Methods 0.000 abstract description 5
- 238000004519 manufacturing process Methods 0.000 abstract description 3
- 229910045601 alloy Inorganic materials 0.000 description 15
- 239000000956 alloy Substances 0.000 description 15
- 230000007797 corrosion Effects 0.000 description 7
- 238000005260 corrosion Methods 0.000 description 7
- 230000000052 comparative effect Effects 0.000 description 6
- 230000009286 beneficial effect Effects 0.000 description 3
- 230000006355 external stress Effects 0.000 description 3
- 238000010438 heat treatment Methods 0.000 description 3
- 230000035945 sensitivity Effects 0.000 description 3
- 238000001816 cooling Methods 0.000 description 2
- 229910018571 Al—Zn—Mg Inorganic materials 0.000 description 1
- 238000003723 Smelting Methods 0.000 description 1
- 230000009471 action Effects 0.000 description 1
- 230000004075 alteration Effects 0.000 description 1
- 238000005266 casting Methods 0.000 description 1
- 238000009792 diffusion process Methods 0.000 description 1
- 239000006185 dispersion Substances 0.000 description 1
- 238000004090 dissolution Methods 0.000 description 1
- 238000005265 energy consumption Methods 0.000 description 1
- 238000000265 homogenisation Methods 0.000 description 1
- 238000001192 hot extrusion Methods 0.000 description 1
- 238000011534 incubation Methods 0.000 description 1
- 239000011159 matrix material Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000006911 nucleation Effects 0.000 description 1
- 238000010899 nucleation Methods 0.000 description 1
- 238000004321 preservation Methods 0.000 description 1
- 239000002994 raw material Substances 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
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- 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
- C22F1/053—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 zinc as the next major constituent
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C21/00—Alloys based on aluminium
- C22C21/10—Alloys based on aluminium with zinc as the next major constituent
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- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Crystallography & Structural Chemistry (AREA)
- Extrusion Of Metal (AREA)
Abstract
The invention relates to the field of aluminum alloy production, in particular to an aging process for improving the texture and performance of a 7N01 aluminum alloy. The method comprises the steps of firstly carrying out natural aging treatment on 7N01 aluminum alloy which is in an extruded state or a rolled state and is subjected to solution treatment, then preserving heat of the 7N01 aluminum alloy at a certain temperature, and applying tensile stress to the aluminum alloy while preserving the heat. By the process, the aging precipitation process of the 7N01 aluminum alloy is improved. The 7N01 aluminum alloy applicable to the invention comprises the following components in percentage by mass: 4.0-5.0%, magnesium: 1.0-2.0%, copper: less than or equal to 0.20 percent, manganese: 0.20 to 0.70%, chromium: less than or equal to 0.30 percent, zirconium: less than or equal to 0.25 percent, titanium: less than or equal to 0.20 percent, vanadium: less than or equal to 0.10 percent, and the balance of aluminum and inevitable impurities. According to the invention, a tensile stress is introduced in the aging process, and the properties of the 7N01 aluminum alloy are obviously improved by improving the morphology of an intragranular precipitated phase and a grain boundary precipitated phase of the 7N01 aluminum alloy.
Description
Technical Field
The invention relates to the field of aluminum alloy production, in particular to an aging process for improving the texture and performance of a 7N01 aluminum alloy.
Background
The 7N01 aluminum alloy is a medium-strength Al-Zn-Mg aluminum alloy for rail transit, and the alloy extruded section is mainly used for bearing parts such as a traction beam, an end beam, a door upright and the like of a high-speed train. The technological process of the alloy extrusion product mainly comprises the following steps: alloy casting, homogenization, hot extrusion, online solution treatment, straightening, aging and the like.
The aging process has great influence on the mechanical property and the stress corrosion sensitivity of the 7N01 aluminum alloy. After the 7N01 aluminum alloy is subjected to peak value aging, an intra-grain precipitated phase has the characteristics of fine dispersion and extremely high number density, so that the alloy has higher mechanical property, but the stress corrosion resistance sensitivity of the alloy is higher due to the fact that the intra-grain precipitated phase is continuous in the state; after the 7N01 aluminum alloy is subjected to overaging treatment, grain boundary precipitated phases are distributed discontinuously, the alloy has good stress corrosion resistance, but the precipitated phases in the grains grow seriously, so that the mechanical property of the alloy is obviously reduced. In contrast, the regression reaging treatment system can enable the alloy to have good stress corrosion resistance while keeping high mechanical property, but the regression reaging system is not suitable for the production of large parts of aluminum alloy because the high-temperature regression time is short. Therefore, designing a reasonable aging process capable of improving the texture and performance of the 7N01 aluminum alloy becomes a hot spot of current research.
Disclosure of Invention
The invention aims to provide an aging process for improving the structure and the performance of a 7N01 aluminum alloy, which improves the aging precipitation process by introducing a tensile stress in the aging process, thereby improving the comprehensive performance of the 7N01 aluminum alloy.
The technical scheme of the invention is as follows:
an aging process for improving the texture and performance of a 7N01 aluminum alloy comprises the following process steps:
firstly, carrying out natural aging on 7N01 aluminum alloy in an extrusion state or a rolling state and subjected to solution treatment for 3-120 days;
and then, preserving the heat of the 7N01 aluminum alloy at 150-170 ℃ for 2-35 hours, and applying a tensile stress of 10-150 MPa to the 7N01 aluminum alloy while preserving the heat.
According to the aging process for improving the texture and the performance of the 7N01 aluminum alloy, the 7N01 aluminum alloy comprises the following components in percentage by mass: 4.0-5.0%, magnesium: 1.0-2.0%, copper: less than or equal to 0.20 percent, manganese: 0.20 to 0.70%, chromium: less than or equal to 0.30 percent, zirconium: less than or equal to 0.25 percent, titanium: less than or equal to 0.20 percent, vanadium: less than or equal to 0.10 percent, and the balance of aluminum and inevitable impurities.
The aging process for improving the texture and the performance of the 7N01 aluminum alloy is preferably used, and the natural aging time is 30-90 days.
The aging process for improving the texture and performance of the 7N01 aluminum alloy is preferable, the heat preservation time is 2-15 hours, and the tensile stress is 75-125 MPa.
According to the aging process for improving the texture and performance of the 7N01 aluminum alloy, the obtained 7N01 aluminum alloy has fine and dispersed precipitated phases and high number density, and the grain boundary precipitated phases are fine and are in discontinuous distribution.
The aging process for improving the texture and performance of the 7N01 aluminum alloy is preferably used, the long axis size range of the in-crystal precipitated phase of the 7N01 aluminum alloy is 8-18 nm, and the number density range of the in-crystal precipitated phase is 3500-6000/mum2The width of the grain boundary precipitated phase is 15-25 nm.
The design idea of the invention is as follows:
the invention changes the thermodynamics and kinetics process of aging precipitation of the 7N01 aluminum alloy by applying an external tensile stress in the aging process. Research results show that the added stress can obviously increase the number of nucleation in the crystal in the aging precipitation process, a large number of cores ensure the number density of precipitated phases in the subsequent aging process, and the high number density of the precipitated phases is beneficial to improving the mechanical property of the alloy; under the action of an external stress, atomic diffusion is inhibited, solute atoms around the grain boundary are difficult to diffuse to the grain boundary, and a grain boundary precipitated phase cannot obtain enough solute atoms from the periphery of the grain boundary to ensure the growth of the grain boundary precipitated phase, so that the grain boundary precipitated phase is fine and discontinuously distributed, and the discontinuous distribution of the grain boundary precipitated phase improves the stress corrosion resistance of the alloy; in addition, the external stress can also inhibit the growth of an intra-crystalline precipitated phase, so that the intra-crystalline precipitated phase of the alloy grows slowly in the subsequent aging process, and the softening of the alloy in the subsequent aging process is inhibited.
The invention has the advantages and beneficial effects that:
1. the invention simplifies the heat treatment process of the 7N01 aluminum alloy and reduces the energy consumption of heat treatment.
2. The invention refines the precipitated phase in the crystal, increases the number of the precipitated phase in the crystal and improves the mechanical property of the alloy.
3. The invention improves the distribution of crystal boundary precipitated phases and is beneficial to reducing the stress corrosion sensitivity.
Drawings
FIG. 1 is a graph of stress aged and stress-free aged hardness versus time at 160 ℃.
FIG. 2 is a TEM morphology of a 7N01 aluminum alloy after 4 hours of stress-free aging treatment.
FIG. 3 is a TEM morphology of a 7N01 aluminum alloy after stress aging for 12 hours.
Detailed Description
In the specific implementation process, the invention firstly carries out natural aging treatment on the 7N01 aluminum alloy which is extruded or rolled and is subjected to solution treatment, then the 7N01 aluminum alloy is kept at a certain temperature, and a tensile stress is applied to the 7N01 aluminum alloy while the temperature is kept. By the process, the aging precipitation process of the 7N01 aluminum alloy is improved.
The process is further described below with reference to examples, but the invention is not limited to these examples.
Example 1
In this example, the implementation process of stress aging of 7N01 aluminum alloy:
1) smelting a 7N01 aluminum alloy raw material in a resistance furnace, wherein the designed 7N01 aluminum alloy comprises the following components in percentage by mass: 4.13%, magnesium: 1.31%, manganese: 0.30%, chromium: 0.21%, zirconium: 0.10%, titanium: 0.06%, and the balance of aluminum and inevitable impurities.
2) And heating the prepared 7N01 aluminum alloy ingot to 470 ℃ in a box-type resistance furnace, preserving heat for 24 hours, and cooling to room temperature in air.
3) Preheating a 7N01 aluminum alloy cast ingot at 450 ℃ for 1 hour, then carrying out extrusion forming, wherein the temperature of an extrusion die is 420 ℃, the extrusion speed is 10m/min, the extrusion ratio is 22, and then immediately cooling to room temperature by water.
4) And naturally aging the extruded 7N01 aluminum alloy plate at room temperature for 60 days.
5) And (3) preserving the heat of the naturally aged 7N01 aluminum alloy at 160 ℃ for different times, and applying 125MPa tensile stress while preserving the heat.
The technical indexes of the embodiment are as follows: hardness of 105-122 HV, intragranular precipitated phaseThe average major axis size is 10-15 nm, and the average precipitated phase number density is 4200-5300/μm2The average width of the grain boundary precipitated phase is 18-22 nm.
Example 2
The difference from the embodiment 1 is that:
1) and naturally aging the extruded 7N01 aluminum alloy plate at room temperature for 30 days.
2) And (3) preserving the heat of the naturally aged 7N01 aluminum alloy at 150 ℃ for different times, and applying 100MPa tensile stress while preserving the heat.
The technical indexes of the embodiment are as follows: the hardness is 98-117 HV, the average long axis size of the precipitated phase in the crystal is 8-14 nm, and the average precipitated phase number density is 4100-4700/mum2The average width of the grain boundary precipitated phase is 16-22 nm.
Example 3
The difference from the embodiment 1 is that:
1) and naturally aging the extruded 7N01 aluminum alloy plate at room temperature for 90 days.
2) And (3) preserving the heat of the naturally aged 7N01 aluminum alloy at 170 ℃ for different times, and applying 75MPa tensile stress while preserving the heat.
The technical indexes of the embodiment are as follows: the hardness is in the range of 101 to 127HV, the average major axis size of the precipitated phase in the crystal is in the range of 11 to 17nm, and the average number density of the precipitated phase is in the range of 4000 to 5100/mum2The average width of the grain boundary precipitated phase is 16-24 nm.
Comparative example
In this comparative example, the difference from example 1 is that: in step 5) of the example, no tensile stress was applied during the 160 ℃ incubation.
The technical indexes of the comparative example are as follows: the hardness is 87-107 HV, the average major axis size of the precipitated phase in the crystal is 30-69 nm, and the average number density of the precipitated phase is 300-850/mum2The average width of the grain boundary precipitated phase is 21-30 nm.
The hardness-time curves of the 7N01 aluminum alloys of the above examples and comparative examples after aging for various periods of time are shown in FIG. 1. As can be seen, the embodiment applies an external stress during the aging process, so that the 7N01 aluminum alloy can obtain higher hardness value, and the hardness value is slowly reduced in the subsequent aging process. The comparative example is a conventional single stage aging with a hardness significantly lower than that of the 7N01 aluminum alloy of the example and a rapid decrease in hardness values during subsequent aging.
FIG. 2 is a TEM morphology of a 7N01 aluminum alloy after 4 hours of stress-free aging. As can be seen, after the stress-free aging treatment, the intragranular precipitated phases are coarse and unevenly distributed, and the grain boundary precipitated phases are coarse and continuously distributed.
FIG. 3 is a TEM morphology of a 7N01 aluminum alloy after 12 hours of stress aging. As can be seen from the figure, after the stress aging treatment, the intragranular precipitated phase is fine and dispersedly distributed in the matrix, thereby increasing more obstacles for dislocation movement and greatly improving the mechanical property of the alloy. In addition, the grain boundary precipitated phase is refined and discontinuously distributed, so that the continuous dissolution of the grain boundary precipitated phase is not facilitated, and the stress corrosion resistance of the alloy is improved.
The results of the examples and the comparative examples show that the invention introduces a tensile stress in the aging process, greatly improves the number density of the intragranular precipitated phase, refines the sizes of the intragranular precipitated phase and the grain boundary precipitated phase, and obviously improves the performance of the 7N01 aluminum alloy.
The above-mentioned embodiments are merely descriptions of technical solutions of the present invention, and the present invention is not limited by the above-mentioned embodiments. Various modifications and alterations of this invention will occur to those skilled in the art without departing from the spirit and scope of this invention as it is designed, and it is intended to cover the appended claims.
Claims (4)
1. An aging process for improving the texture and the performance of a 7N01 aluminum alloy is characterized by comprising the following process steps:
firstly, carrying out natural aging on 7N01 aluminum alloy in an extrusion state or a rolling state and subjected to solution treatment for 3-120 days;
then, preserving the heat of the 7N01 aluminum alloy at 150-170 ℃ for 2-35 hours, and applying a tensile stress of 10-150 MPa to the 7N01 aluminum alloy while preserving the heat;
the obtained 7N01 aluminum alloy has fine and dispersed precipitated phases in the crystal and high number density, and the precipitated phases in the crystal boundary are fine and are in discontinuous distribution;
the long axis size range of the in-crystal precipitated phase of the 7N01 aluminum alloy is 8-18 nm, and the number density range of the in-crystal precipitated phase is 3500-6000/mum2The width of the grain boundary precipitated phase is 15-25 nm.
2. The aging process for improving the texture and performance of a 7N01 aluminum alloy according to claim 1, wherein the composition of the 7N01 aluminum alloy is, in terms of element mass percent, Zn: 4.0-5.0%, magnesium: 1.0-2.0%, copper: less than or equal to 0.20 percent, manganese: 0.20 to 0.70%, chromium: less than or equal to 0.30 percent, zirconium: less than or equal to 0.25 percent, titanium: less than or equal to 0.20 percent, vanadium: less than or equal to 0.10 percent, and the balance of aluminum and inevitable impurities.
3. The aging process for improving the texture and performance of a 7N01 aluminum alloy according to claim 1, wherein the natural aging time is 30-90 days.
4. The aging process for improving the structure and the performance of 7N01 aluminum alloy according to claim 1, wherein the holding time is 2-15 hours, and the tensile stress is 75-125 MPa.
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| CN112301300B (en) * | 2020-11-02 | 2022-03-18 | 安徽工业大学 | Preparation method of high-strength corrosion-resistant magnesium alloy plate |
| CN114107753B (en) * | 2021-10-08 | 2022-10-11 | 中国科学院金属研究所 | Design method of 6082 aluminum alloy without parking effect |
| CN115161524B (en) * | 2022-09-08 | 2022-11-29 | 北京科技大学 | Stress corrosion resistant high-strength aluminum alloy and preparation method thereof |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH01279723A (en) * | 1988-04-30 | 1989-11-10 | Fukuda Metal Foil & Powder Co Ltd | Cu-zn-al sintered superelastic alloy and its manufacture |
| JP2002220648A (en) * | 2001-01-24 | 2002-08-09 | Togo Seisakusho Corp | Coiled spring made from aluminum alloy and manufacturing method therefor |
| KR20070000050A (en) * | 2005-06-27 | 2007-01-02 | 카야바 고교 가부시기가이샤 | Aluminum alloy pipe and method for manufacturing the same |
| JP2009221567A (en) * | 2008-03-18 | 2009-10-01 | Furukawa-Sky Aluminum Corp | Aluminum alloy sheet for positive pressure coated can lid, and method for producing the same |
| CN103540883A (en) * | 2013-10-16 | 2014-01-29 | 河南科技大学 | Aging treatment method for lowering residual stress of copper alloy wire |
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Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH01279723A (en) * | 1988-04-30 | 1989-11-10 | Fukuda Metal Foil & Powder Co Ltd | Cu-zn-al sintered superelastic alloy and its manufacture |
| JP2002220648A (en) * | 2001-01-24 | 2002-08-09 | Togo Seisakusho Corp | Coiled spring made from aluminum alloy and manufacturing method therefor |
| KR20070000050A (en) * | 2005-06-27 | 2007-01-02 | 카야바 고교 가부시기가이샤 | Aluminum alloy pipe and method for manufacturing the same |
| JP2009221567A (en) * | 2008-03-18 | 2009-10-01 | Furukawa-Sky Aluminum Corp | Aluminum alloy sheet for positive pressure coated can lid, and method for producing the same |
| CN103540883A (en) * | 2013-10-16 | 2014-01-29 | 河南科技大学 | Aging treatment method for lowering residual stress of copper alloy wire |
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