CN104404414A - 7075 aluminum alloy plate creep age forming method - Google Patents
7075 aluminum alloy plate creep age forming method Download PDFInfo
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- CN104404414A CN104404414A CN201410741289.2A CN201410741289A CN104404414A CN 104404414 A CN104404414 A CN 104404414A CN 201410741289 A CN201410741289 A CN 201410741289A CN 104404414 A CN104404414 A CN 104404414A
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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
Abstract
The invention discloses a 7075 aluminum alloy plate creep age forming method. The method comprises the following steps: (1) carrying out solid-solution treatment on a 7075 aluminum alloy plate with a thickness of 2-40 mm for 30-90 minutes at a temperature of 466-480 DEG C, then water-quenching, subsequently carrying out 1-5 percent of pre-deformation and finally carrying out artificial aging treatment for 6-24 hours at a temperature of 80-120 DEG C; (2) carrying out retrogression treatment, wherein the retrogression treatment temperature is 160-200 DEG C, and the heat preservation time is 20-180 minutes, and then carrying out water quenching at a room temperature; (3) carrying out 1-5 percent of pre-deformation on the plate subjected to the retrogression treatment, then placing the plate in a mould and fixing; (4) carrying out creep age forming, wherein the creep age forming temperature is 120-160 DEG C, the applied stress is 200-260 MPa, and the forming time is 12-24 hours; (5) unloading the plate from the mould. When the method disclosed by the invention is utilized for processing the 7075 aluminum alloy plate, while the strength of the aluminum alloy plate is ensured, the corrosion resistance of the 7075 aluminum alloy plate can be effectively improved.
Description
Technical field
The present invention relates to a kind of creep age forming method of 7075 aluminum alloy plate materials, belong to nonferrous materials processing engineering technology field.
Technical background
7075 aluminium alloys belong to heat-treatable strengthened aldural, have higher strong/advantage such as anharmonic ratio, good hot workability and high fatigue toughness, become the critical material of modern aerospace equipment, be widely used in the manufacture of aircraft wing skins and fuselage skin.In recent years, aircraft structure is constantly to lightweight, and the long lifetime, high reliability future development, military service performance also little by little rushing into extremes, therefore proposes very high requirement to forming technique.Integral panel manufacturing technology is the study hotspot of aerospace part in recent years, and creep age forming method is the desirable technique manufacturing complicated band muscle and Varying-thickness integral panel.Adopt the Varying-thickness large size integral panel of the method manufacture to have the advantages such as forming accuracy is high, unrelieved stress is little, the manufacturing cycle is short, significantly can reduce production cost simultaneously.Research shows, the main strengthening phase of 7075 aluminium alloys is η ' phase (MgZn
2), only adopt artificial aging and creep ageing method, although can obtain higher yield strength, alloy corrosion resistance can be poor.When 7075 aluminium alloys of usual employing multistage aging system process have good toughness and solidity to corrosion, but its strength degradation 10 ~ 15%.Alloy components prepared by aforesaid method all cannot meet actual service demand, and in forming process, there is the shortcomings such as unrelieved stress is high, forming period is long.Therefore a kind of novel method being suitable for 7075 aluminum alloy plate materials creep age formings is badly in need of, to obtaining good shape/property cooperative development in integral panel forming process.
Summary of the invention
The object of the present invention is to provide a kind of applicable integrally formed creep ageing method of 7075 aluminum alloy plate materials, solve the shape/property cooperative development in current integral panel forming process, improve the bottleneck problem of mechanical property and corrosion resistance simultaneously.
For achieving the above object, the technical solution used in the present invention is: a kind of by the intracrystalline ageing strengthening phase of regulation and control 7075 aluminium alloy, the creep age forming method of precipitate free zone.The concrete steps of the method are:
Step 1: the solution treatment 7075 aluminum alloy plate materials that 2 ~ 40mm is thick being carried out under 466 ~ 480 DEG C of temperature condition to 30 ~ 90 minutes, then shrend, carries out the predeformation of 1 ~ 5% subsequently, finally carries out 80 ~ 120 DEG C, the artificial aging process of 6 ~ 24 hours;
Step 2: carry out regression treatment to the sheet alloy after step 1 processes, the temperature of regression treatment is 160 ~ 200 DEG C, and soaking time is 20 ~ 180 minutes, then carries out room temperature shrend;
Step 3: carry out 1 ~ 5% predeformation to the sheet alloy after step 2 processes, is then placed in mould and fixes by sheet material;
Step 4: carry out creep age forming to the sheet alloy processed through step 3, creep age forming temperature is 120 ~ 160 DEG C, and applied stress is 200 ~ 260MPa, and curring time is 12 ~ 24 hours.
Step 5: unload sheet material from mould.
The present invention has following consideration in thermal treatment: by solid solution, quenching, predeformation and artificial aging process, eliminate unrelieved stress, simultaneously introducing portion dislocation in the alloy, make ageing strengthening abundant forming core mutually in alloy, after artificial aging, alloy intracrystalline obtains the precipitated phase of small and dispersed, and grain boundaries obtains the precipitated phase of the comparatively large also continuous distribution of size; In regression treatment, the strengthening phase of alloy intracrystalline small and dispersed is dissolved in matrix again, Grain Boundary Precipitates generation alligatoring; By second time predeformation, sheet material internal residual stress is discharged, simultaneously introducing portion dislocation.In creep ageing process, intracrystalline precipitated phase is separated out again, the further alligatoring of grain boundary precipitate, the precipitation state of the change controllable strengthening phase of aging temp and plus load, impel alloy matrix precipitate to be the feature that small and dispersed distributes, and Grain Boundary Precipitates is characterized by discontinuously arranged state.This processing mode has regulated and controled the pick-up behavior of precipitated phase well, while proof strength, effectively improves the corrosion resistance nature of aluminum alloy plate materials.
The present invention adopts above scheme, has following characteristics: this invention has carried out recurrence and creep ageing process to 7075 aluminum alloy plate materials.In regressive process, intracrystalline Age-prrcipitation Phase back dissolving, Grain Boundary Precipitates alligatoring; In creep ageing process, again regulated and controled pick-up behavior and the distribution of precipitated phase by the change in the external heat field of force.Compare artificial aging and other creep ageing, the method is simple to operate, Be very effective, is conducive to, while guarantee 7075 aluminum alloy plate materials intensity, significantly improving its corrosion resistance nature, can save material simultaneously, shortens the production cycle.
The hardness of indication aluminum alloy plate materials of the present invention is on TMVS-1 Vickers hardness tester, adopt trying hard to keep of 2.94N to carry test in 15 seconds.Electrokinetic potential cyclic polarization corrosion test is carried out on CHI660E electrochemical workstation.
Accompanying drawing explanation
The schema of Fig. 1 the inventive method processing sample
The TEM light field phase photo of Figure 27 075 aluminium alloy: (a), (b) are intracrystalline without the inventive method process and Grain Boundary Precipitates figure; C (), (d) are intracrystalline through the inventive method process and Grain Boundary Precipitates figure
The galvanic corrosion pattern SEM of Figure 37 075 aluminium alloy schemes: (a), (b) are the erosion profile figure without the inventive method process; C (), (d) are the erosion profile figure through process of the present invention
Embodiment
Below in conjunction with the drawings and specific embodiments, the present invention is described in detail.
The present invention is a kind of creep age forming method of 7075 aluminum alloy plate materials, for 7075 aluminium alloys of alloying constituent shown in table 1, introduces the creep age forming method that the present invention relates in detail.The Vickers' hardness that in each example, hardness test adopts GB/T4340.4-2009 to carry out test materials measures.Electrochemical corrosion performance test of the present invention adopts GB/T24196-2009 to carry out the test of dynamic potential polarization curve.
The alloying constituent (wt.%) of material therefor in table 1 example of the present invention
Embodiment 1
A 3mm heavy-gauge sheeting adopts 470 DEG C of solution treatment to carry out shrend after 1 hour, carry out subsequently 3% predeformation and 120 DEG C, the artificial aging process of 24 hours.Returning temperature is 185 DEG C, and heating rate is 10 DEG C/min, returns insulation and carries out shrend immediately after 20 minutes.Carry out the predeformation of 3%.Creep ageing temperature is 120 DEG C, and applied stress is 260MPa, and curring time is 24 hours.
Embodiment 2
B 3mm heavy-gauge sheeting adopts 470 DEG C of solution treatment to carry out shrend after 1 hour, carry out subsequently 3% predeformation and 120 DEG C, the artificial aging process of 24 hours.Returning temperature is 185 DEG C, and heating rate is 10 DEG C/min, returns insulation and carries out shrend immediately after 40 minutes.Carry out the predeformation of 3%.Creep ageing temperature is 120 DEG C, and applied stress is 260MPa, and curring time is 24 hours.
Embodiment 3
C 3mm heavy-gauge sheeting adopts 470 DEG C of solution treatment to carry out shrend after 1 hour, carry out subsequently 3% predeformation and 120 DEG C, the artificial aging process of 24 hours.Returning temperature is 185 DEG C, and heating rate is 10 DEG C/mm, returns insulation and carries out shrend immediately after 60 minutes.Carry out the predeformation of 3%.Creep ageing temperature is 120 DEG C, and applied stress is 260MPa, and curring time is 24 hours.
Comparative example
D 3mm heavy-gauge sheeting adopts 470 DEG C of solution treatment to carry out shrend after 1 hour, carries out the pre-treatment of 3% subsequently, then carries out creep age forming.Creep ageing temperature is 120 DEG C, and applied stress is 260MPa, and curring time is 24 hours.
Fig. 2 (a) and (b) are sheet alloy intracrystalline without the inventive method process and Grain Boundary Precipitates light field phasor.As can be seen from the figure, the precipitated phase of small and dispersed is evenly distributed in intracrystalline, and Grain Boundary Precipitates is comparatively thick, and in continuous distribution state; Fig. 2 (c) and (d) are sheet alloy intracrystalline through the inventive method process and Grain Boundary Precipitates light field phasor.As can be seen from the figure, its matrix precipitate is similar to the matrix precipitate without the inventive method process, but the obvious alligatoring of Grain Boundary Precipitates, in discontinuously arranged state, and there is wider precipitate free zone.Therefore, after the inventive method process, the intensity of 7075 aluminum alloy plate materials does not significantly decrease, but its corrosion resistance nature significantly improves (as shown in table 2 and table 3).
Fig. 3 (a) and (b) are the sheet alloy erosion profile figure without the inventive method process.As can be seen from the figure, alloy there occurs serious corrosion, have the point corrosion pit of large-size to occur, and point corrosion pit is polymerized at plate surface.Fig. 3 (a) and (b) are the sheet alloy erosion profile figure without the inventive method process.As can be seen from the figure, sheet alloy surface only has a small amount of isolated point corrosion pit to occur, and the size of point corrosion pit is less, and the degree of depth is more shallow.Therefore, after the inventive method process, the corrosion resistance nature of 7075 aluminum alloy plate materials significantly improves.
Table 2 gives the hardness value, corrosion potential, pitting potential and the precipitate free zone width that use embodiment of the present invention interalloy.Table 3 gives the hardness value of comparative example's interalloy, corrosion potential, pitting potential and precipitate free zone width.It can thus be appreciated that creep age forming method of the present invention can effectively guarantee desirable mechanical property and corrosion resistance nature.
Table 2 uses the hardness value of embodiment of the present invention interalloy, corrosion potential, pitting potential and precipitate free zone width
The hardness value of table 3 comparative example interalloy, corrosion potential, pitting potential and precipitate free zone width
Claims (9)
1. 7075 aluminum alloy plate materials creep age forming methods, is characterized in that: utilize the creep ageing characteristic of 7075 aluminium alloys to realize the shaping of sheet material, and obtain desirable over-all properties, the method comprises the following steps:
Step 1: carry out solution treatment to 7075 aluminum alloy plate materials, then shrend, carries out predeformation subsequently, finally carries out artificial aging process;
Step 2: regression treatment is carried out to the sheet alloy after step 1 processes, then carries out room temperature shrend;
Step 3: carry out predeformation to the sheet alloy after step 2 processes, is then placed in mould and fixes by sheet material;
Step 4: creep age forming is carried out to the sheet alloy processed through step 3;
Step 5: unload sheet material from mould.
2. the method for claim 1, is characterized in that: the thickness of 7075 aluminum alloy plate materials described in step 1 is 2 ~ 40mm.
3. the method for claim 1, is characterized in that: the solid solution temperature described in step 1 is 466 ~ 480 DEG C, and the solution treatment time is 30 ~ 90 minutes.
4. the method for claim 1, is characterized in that: the predeformation amount described in step 1 is 1 ~ 5%.
5. the method for claim 1, is characterized in that: the treatment temp of artificial aging described in step 1 is 80 ~ 120 DEG C, and the artificial aging treatment time is 6 ~ 24 hours.
6. the method for claim 1, is characterized in that: the regression treatment temperature described in step 2 is 160 ~ 200 DEG C, and soaking time is 20 ~ 180 minutes.
7. the method for claim 1, is characterized in that: the predeformation amount described in step 3 is 1 ~ 5%.
8. the method for claim 1, is characterized in that: the creep age forming temperature described in step 4 is 120 ~ 160 DEG C, and applied stress is 200 ~ 260MPa, and curring time is 12 ~ 24 hours.
9. the method for claim 1, is characterized in that: the vickers hardness number (HV) of the final sheet alloy obtained is 176.0 to 189.5, and corrosion potential is-0.752V
sCEto-0.716V
sCE, pitting potential is-0.697V
sCEto-0.681V
sCE, precipitate free zone width is 14.3nm to 37.5nm.
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Cited By (11)
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| CN105033009A (en) * | 2015-07-02 | 2015-11-11 | 芜湖长鹏汽车零部件有限公司 | Aluminum plate performing technology |
| CN106435417A (en) * | 2016-10-27 | 2017-02-22 | 福州大学 | Multistage deformation aging method for improving overall performance of 7xxx series aluminium alloy |
| CN107447172A (en) * | 2017-09-26 | 2017-12-08 | 常熟市恒泰精密金属制品有限公司 | The heat treatment method of aluminum alloy plate materials |
| CN108265246A (en) * | 2018-01-25 | 2018-07-10 | 湖南大学 | A kind of method for improving intensity non-uniformity after 7 line aluminium alloy of large scale quenches |
| CN108486508A (en) * | 2018-02-07 | 2018-09-04 | 中南大学 | A kind of efficient creep age forming method of aluminium alloy |
| CN109402539A (en) * | 2018-11-29 | 2019-03-01 | 四川航天长征装备制造有限公司 | A method of it improving rods and bars of aluminium alloy and radially extends rate |
| CN109487186A (en) * | 2018-12-28 | 2019-03-19 | 中南大学 | A kind of method of creep age forming aluminium alloy element shape/property collaboration optimization |
| CN109570321A (en) * | 2018-11-26 | 2019-04-05 | 中南大学 | A method of for promoting creep forming |
| CN109628813A (en) * | 2019-01-02 | 2019-04-16 | 中南大学 | A method of improving magnesium-rare earth high temperature creep-resistant property using high density pollution freemetallurgy |
| CN111940576A (en) * | 2020-07-15 | 2020-11-17 | 北京宇航系统工程研究所 | Preparation method of aluminum alloy complex component product with bidirectional curvature |
| CN112267082A (en) * | 2020-09-10 | 2021-01-26 | 西北工业大学 | Alloy plate pulse current regression creep age forming method |
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Cited By (17)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105033009A (en) * | 2015-07-02 | 2015-11-11 | 芜湖长鹏汽车零部件有限公司 | Aluminum plate performing technology |
| CN106435417A (en) * | 2016-10-27 | 2017-02-22 | 福州大学 | Multistage deformation aging method for improving overall performance of 7xxx series aluminium alloy |
| CN106435417B (en) * | 2016-10-27 | 2018-06-15 | 福州大学 | A kind of multistage deformation aging process for improving 7xxx line aluminium alloy comprehensive performances |
| CN107447172A (en) * | 2017-09-26 | 2017-12-08 | 常熟市恒泰精密金属制品有限公司 | The heat treatment method of aluminum alloy plate materials |
| CN108265246A (en) * | 2018-01-25 | 2018-07-10 | 湖南大学 | A kind of method for improving intensity non-uniformity after 7 line aluminium alloy of large scale quenches |
| CN108486508B (en) * | 2018-02-07 | 2020-09-01 | 中南大学 | Efficient creep age forming method for aluminum alloy |
| CN108486508A (en) * | 2018-02-07 | 2018-09-04 | 中南大学 | A kind of efficient creep age forming method of aluminium alloy |
| CN109570321A (en) * | 2018-11-26 | 2019-04-05 | 中南大学 | A method of for promoting creep forming |
| CN109570321B (en) * | 2018-11-26 | 2020-06-26 | 中南大学 | Method for promoting creep forming |
| CN109402539A (en) * | 2018-11-29 | 2019-03-01 | 四川航天长征装备制造有限公司 | A method of it improving rods and bars of aluminium alloy and radially extends rate |
| CN109402539B (en) * | 2018-11-29 | 2020-02-11 | 四川航天长征装备制造有限公司 | Method for improving radial elongation of aluminum alloy bar |
| CN109487186A (en) * | 2018-12-28 | 2019-03-19 | 中南大学 | A kind of method of creep age forming aluminium alloy element shape/property collaboration optimization |
| CN109487186B (en) * | 2018-12-28 | 2021-02-02 | 中南大学 | Method for shape/performance collaborative optimization of creep age forming aluminum alloy component |
| CN109628813A (en) * | 2019-01-02 | 2019-04-16 | 中南大学 | A method of improving magnesium-rare earth high temperature creep-resistant property using high density pollution freemetallurgy |
| CN109628813B (en) * | 2019-01-02 | 2021-05-28 | 中南大学 | Method for improving high-temperature creep resistance of rare earth magnesium alloy by using high-density precipitate-free zone |
| CN111940576A (en) * | 2020-07-15 | 2020-11-17 | 北京宇航系统工程研究所 | Preparation method of aluminum alloy complex component product with bidirectional curvature |
| CN112267082A (en) * | 2020-09-10 | 2021-01-26 | 西北工业大学 | Alloy plate pulse current regression creep age forming method |
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