CN103305779A - Thermomechanical treatment method of 6000-series aluminum alloy - Google Patents
Thermomechanical treatment method of 6000-series aluminum alloy Download PDFInfo
- Publication number
- CN103305779A CN103305779A CN2013102430599A CN201310243059A CN103305779A CN 103305779 A CN103305779 A CN 103305779A CN 2013102430599 A CN2013102430599 A CN 2013102430599A CN 201310243059 A CN201310243059 A CN 201310243059A CN 103305779 A CN103305779 A CN 103305779A
- Authority
- CN
- China
- Prior art keywords
- carry out
- preageing
- aluminum alloy
- alloy
- treatment method
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Images
Landscapes
- Printing Plates And Materials Therefor (AREA)
- Metal Rolling (AREA)
Abstract
The invention belongs to the technical field of an aluminum alloy thermomechanical treatment, which is particularly suitable for a 6000-series aluminum alloy. The invention provides a thermomechanical treatment method of a 6000-series aluminum alloy, aiming at the defect that in the prior art, the peak value aging state (T6) of the 6000-series aluminum alloy is high in strength and the intercrystalline corrosion is severe, so that not only the intensity of the 6000-series aluminum alloy can be improved greatly, but also the intercrystalline corrosion sensitivity is eliminated. The technical scheme provided by the invention particularly comprises the following step of: treating the 6000-series aluminum alloy sequentially in the following steps of: (1) solution treatment; (2) quenching; (3) pre-aging; (4) cold rolling and deforming; and (5) re-aging.
Description
Technical field
The invention belongs to aluminium alloy thermomechanical treatment technology field, be particularly useful for 6000 line aluminium alloys.
Background technology
6000 line aluminium alloys belong to ageing strengthening type alloy, such as 6061,6056,6082,6013,6063 etc., have the characteristics such as low density, medium tenacity and weldability and good forming ability, be widely used in the industry such as space flight and aviation, traffic, building and machinofacture.In order to obtain high strength, the industrial T6 that often carries out processes (peak value timeliness), to farthest form high-density nano level precipitated phase in aluminum substrate, such as GP district, β ", β ', Q ' etc., thereby the highest alloy strength of acquisition.When yet T6 processed, on the one hand, Grain Boundary Precipitates was continuous regime and distributes, and jointly formed the continuous corrosion microbattery with the crystal boundary of continuous distribution without separating out district (PFZ); On the other hand, crystal boundary also forms the continuous corrosion microbattery without separating out between district and the matrix.Corrosion microbattery in the crystal boundary area of these two kinds of forms causes 6000 to be associated gold to have serious Susceptibility To Intergranular Corrosion under the T6 state, is associated the range of application of gold thereby significantly restricted this.
In order to improve 6000 corrosion among crystalline grains that are associated gold, industrially usually adopt overaging to process (T7).Carry out the T7 processing by improving aging temp and prolonging aging time.Under the overaging state, Grain Boundary Precipitates generation alligatoring and be discontinuously arranged causes interrupted Grain Boundary Precipitates and the crystal boundary that distributes no longer to form the continuous corrosion microbattery between the district without separating out; In addition, overaging is processed and can be caused equally the matrix solute atoms fully to separate out with the matrix precipitated phase seriously to grow up, cause matrix and crystal boundary to corrode microbattery without separating out also no longer to form between the district.Therefore, overaging can be eliminated the Susceptibility To Intergranular Corrosion of alloy.But overaging is processed and is caused the matrix precipitated phase seriously to grow up, and can cause alloy strength significantly to descend, and this is unfavorable for again the improvement of alloy mechanical property on the contrary.Therefore, if can develop the intensity that is not less than or even is higher than the T6 state, can eliminate again the deformation heat treatment method of its Susceptibility To Intergranular Corrosion simultaneously, significant for promoting 6000 line aluminium alloy performance potential and enlarging its range of application.
As previously mentioned, for 6000 being age hardening type aluminium alloy, obtain high strength and high anti-corrosion, will satisfy then that the matrix precipitate size is little, density is high, and the thick and interrupted distribution of Grain Boundary Precipitates.Yet this tissue signature is difficult to only obtain by ageing treatment.
Summary of the invention
Though the present invention overcomes 6000 line aluminium alloy peak ageds (T6) in the prior art intensity height and this serious deficiency of Susceptibility To Intergranular Corrosion, a kind of deformation heat treatment method of 6000 line aluminium alloys is provided, by preageing, the cold roller and deformed and method that combines of timeliness again, can increase substantially on the 6000 line aluminium alloy intensity bases, can eliminate Susceptibility To Intergranular Corrosion again simultaneously.
The technical solution used in the present invention is as follows: a kind of deformation heat treatment method of 6000 line aluminium alloys, and step is: 6000 line aluminium alloys are processed through following steps successively: (1) solution treatment; (2) quench; (3) preageing; (4) cold roller and deformed; (5) timeliness again.
Solution treatment is the alloying elements such as Mg, Si, Cu to be dissolved in matrix form the high temperature solid solution body, influence factor comprises solid solubility temperature and solution time, its parameter is selected based on following principle: both guaranteed that alloying element fully dissolved in matrix and forms solute atoms, and do not caused again grain-size too to grow up or burning.In general, solid solubility temperature is higher, then can select shorter soaking time, and vice versa.As preferably, the described solution treatment of step (1), solid solubility temperature is 530 ℃-560 ℃, solution time is 1-4h.
The purpose of quenching is that the high temperature solid solution body is cooled down fast, forms the room temperature supersaturated solid solution.As preferably, the described quenching mode of step (2) mainly adopts water-cooled or air cooling way.
The purpose of preageing be with the aluminium alloy timeliness to lack time effect or peak aged, thereby precipitation strength phase in aluminum substrate in advance obtains precipitating reinforcing effect, major influence factors comprises aging temp and aging time.As preferably, the described aging temp of step (3) is 150 ℃-190 ℃, and aging time is 1-24h, by the reasonable coordination of aging temp and aging time, so that alloy is in lack time effect or peak aged.In general, aging temp is lower, and then aging time is longer, and aging temp is higher, and then aging time is shorter.
The aluminium alloy of Pre-aging treatment is carried out at normal temperatures cold roller and deformed, purpose is to introduce additional working hardening effect on the precipitation strength basis.In order to obtain larger working hardening effect, as preferably, the described minimum cold rolling reduction of step (4) is generally greater than 60%, maximum deformation quantity then will take guarantee when cold roller and deformed alloy not cracking as prerequisite.
As preferably, described deflection is determined according to the preageing hardenability: when the preageing hardenability is low, usually select larger deflection; When the preageing hardenability is higher, the less deflection of general selection.
Cold roller and deformed alloy is carried out again ageing treatment, its objective is and adjust matrix and Grain Boundary Precipitates feature, major influence factors comprises aging temp and aging time.As preferably, the described again aging temp of step (5) is 160 ℃-230 ℃, and aging time is 1-12h again.During ageing treatment, aging temp is higher again, then will select shorter again aging time again, and vice versa.Design parameter needs to select according to the intergranular corrosion experimental result usually.
Beneficial effect of the present invention is as follows: the present invention can realize increasing substantially on the 6000 line aluminium alloy intensity bases by preageing, cold deformation and the method that combines of timeliness again, can eliminate Susceptibility To Intergranular Corrosion again simultaneously.
Description of drawings
Fig. 1 the present invention is out of shape the thermal treatment schematic diagram;
Fig. 2 erosion profile figure, (a) be 6061 corrosion of aluminium alloy patterns after the ageing treatment of conventional 540 ℃/1h solution treatment, shrend and T6(180 ℃/6h), (b) be 540 ℃/1h of the present invention solution treatment, shrend and 180 ℃/2h+75% cold roller and deformed+6061 corrosion of aluminium alloy patterns after the 175 ℃/6h processing;
Fig. 3 crystal boundary area organization chart, (a) be 6061 aluminium alloy crystal boundary area tissues after the ageing treatment of conventional 540 ℃/1h solution treatment, shrend and T6(180 ℃/6h), (b) be 540 ℃/1h of the present invention solution treatment, shrend and 180 ℃/2h+75% cold roller and deformed+6061 aluminium alloy crystal boundary area tissues after the 175 ℃/6h processing;
Fig. 4 stretching fracture shape appearance figure, (a) be 6061 aluminium alloy stretching fracture patterns after the ageing treatment of conventional 540 ℃/1h solution treatment, shrend and T6(180 ℃/6h), (b) be 540 ℃/1h of the present invention solution treatment, shrend and 180 ℃/2h+75% cold roller and deformed+6061 aluminium alloy stretching fracture patterns after the 175 ℃/6h processing.
Embodiment
The present invention is take three kinds of aluminum alloy hot rolling sheet materials such as 6061,6082,6013 as example, and original plate thickness is 4mm.Tensile property testing method: by the test of GB GB/T24182-2009(Metal Mechanic Property), carry out at the WDT-30 tensile testing machine.Intergranular corrosion testing method: by GB GB/T7998-2005(aluminium alloy intergranular corrosion measuring method) carries out, carry out erosion profile at the XJG-05 metaloscope and observe.The stretching fracture morphology observation is carried out in the JSM-6510 scanning electron microscope.Microstructure observation is at FEI G
2Carry out on 20 transmission electron microscopes.
Fig. 1 is that the present invention is out of shape the process of thermal treatment schematic flow sheet, comprises for 5 stages: solution treatment, and solid solubility temperature is at 530 ℃-560 ℃, and soaking time is 1-4h, guarantees that alloying element fully is dissolved in aluminum substrate; Quench, water-cooled or air-cooled is guaranteed not separate out in the process of cooling; Preageing, aging temp are 150 ℃-190 ℃, and aging time guarantees that at 1-24h alloy is in lack time effect or peak aged; Cold roller and deformed, deflection will be guaranteed not cracking of alloy more than 60%; Timeliness again, temperature is at 160-230 ℃, and the time guarantees that at 1-12h alloy is without Susceptibility To Intergranular Corrosion.
Comparative example 1:
6061 aluminum alloy hot rolling sheet materials, after 540 ℃/1h solution treatment and shrend, 180 ℃/6h timeliness is to peak value T6 state.At this moment, alloy tensile property and form of corrosion see Table 1, and erosion profile is seen Fig. 2 a, and the crystal boundary area tissue is seen Fig. 3 a, and the stretching fracture pattern is seen Fig. 4 a.
Embodiment 1:
6061 aluminum alloy hot rolling sheet materials after 540 ℃/1h solution treatment and shrend, at first carry out 180 ℃/2h preageing, carry out afterwards draught and be 75% cold rolling at room temperature distortion, carry out at last 175 ℃/6h timeliness again.At this moment, alloy tensile property and form of corrosion see Table 1, and erosion profile is seen Fig. 2 b, and crystal boundary area transmission electron microscope tissue is seen Fig. 3 b, and the stretching fracture pattern is seen Fig. 4 b.
Fig. 2 be the ageing treatment of conventional 540 ℃/1h solution treatment, shrend and T6(180 ℃/6h) and 180 ℃/2h+75% cold roller and deformed+6061 corrosion of aluminium alloy patterns under the 175 ℃/6h two states.Fig. 2 a shows, T6 state 6061 aluminium alloy intergranules are separated from each other, and presents serious intergranular corrosion tendency.And through 540 ℃/1h of the present invention solution treatment, shrend and 180 ℃/2h+75% cold roller and deformed+175 ℃/6h processes (Fig. 2 b), clearly, alloy has been eliminated Susceptibility To Intergranular Corrosion fully, presents uniform corrosion.
Fig. 3 provided the ageing treatment of conventional 540 ℃/1h solution treatment, shrend and T6(180 ℃/6h) and 540 ℃/1h solution treatment, shrend and 180 ℃/2h+75% cold roller and deformed+6061 aluminium alloy crystal boundary area tissues under the 175 ℃/6h two states, Fig. 3 a shows, after the T6 timeliness, the matrix precipitated phase mainly is spherical GP district and acicular beta " then be the thick strip Q phase that is continuous distribution mutually, on the crystal boundary; And after 540 ℃/1h of the present invention solution treatment, shrend and 180 ℃/2h+75% cold deformation+175 ℃/6h processes (Fig. 3 b), the matrix precipitated phase mainly is lath-shaped Q ' phase, the dislocation that contains simultaneously higher density, and the Grain Boundary Precipitates form also changes interrupted the distribution by the continuous distribution of T6 state.This Microstructure characteristics has good anti intercrystalline corrosion performance simultaneously so that 6061 aluminium alloys have high tensile property just.
Fig. 4 provided the ageing treatment of conventional 540 ℃/1h solution treatment, shrend and T6(180 ℃/6h) and 540 ℃/1h solution treatment, shrend and 540 ℃/1h solution treatment, shrend and 180 ℃/2h+75% cold roller and deformed+6061 aluminium alloy stretching fracture patterns under the 175 ℃/6h two states.Can find out, the alloy stretching fracture all is typical dimple type transgranular fracture mode under two kinds of states, shows that the alloy of processing through the present invention still has good unit elongation, and data have also confirmed this point in the table 1.
Embodiment 2:
6061 aluminum alloy hot rolling sheet materials, through 530 ℃/1h solution treatment and air-cooled after, at first carry out 150 ℃/24h preageing, carry out afterwards draught and be 80% cold rolling at room temperature distortion, carry out again at last 160 ℃/12h timeliness.At this moment, alloy tensile property and form of corrosion see Table 1.
Embodiment 3:
6061 aluminum alloy hot rolling sheet materials after 530 ℃/4h solution treatment and shrend, at first carry out 190 ℃/1h preageing, carry out afterwards draught and be 60% cold rolling at room temperature distortion, carry out at last again timeliness of 170 ℃/10h again.At this moment, alloy tensile property and form of corrosion see Table 1.
Embodiment 4:
6061 aluminum alloy hot rolling sheet materials after 560 ℃/4h solution treatment and shrend, at first carry out 170 ℃/8h preageing, carry out afterwards draught and be 90% cold rolling at room temperature distortion, carry out at last again timeliness of 180 ℃/8h.At this moment, alloy tensile property and form of corrosion see Table 1.
Embodiment 5:
6061 aluminum alloy hot rolling sheet materials after 550 ℃/4h solution treatment and shrend, at first carry out 190 ℃/4h preageing, carry out afterwards draught and be 60% cold rolling at room temperature distortion, carry out at last again timeliness of 190 ℃/6h again.At this moment, alloy tensile property and form of corrosion see Table 1.
Embodiment 6:
6061 aluminum alloy hot rolling sheet materials, through 550 ℃/1h solution treatment and air-cooled after, at first carry out 150 ℃/12h preageing, carry out afterwards draught and be 60% cold rolling at room temperature distortion, carry out again at last again timeliness of 200 ℃/4h.At this moment, alloy tensile property and form of corrosion see Table 1.
Embodiment 7:
6061 aluminum alloy hot rolling sheet materials after 540 ℃/2h solution treatment and shrend, at first carry out 190 ℃/4h preageing, carry out afterwards draught and be 80% cold rolling at room temperature distortion, carry out at last again timeliness of 220 ℃/2h again.At this moment, alloy tensile property and form of corrosion see Table 1.
Embodiment 8:
6061 aluminum alloy hot rolling sheet materials, through 560 ℃/1h solution treatment and air-cooled after, at first carry out 160 ℃/12h preageing, carry out afterwards draught and be 70% cold rolling at room temperature distortion, carry out again at last again timeliness of 230 ℃/1h.At this moment, alloy tensile property and form of corrosion see Table 1.
Comparative example 2:
6082 aluminum alloy hot rolling sheet materials after 560 ℃/1h solution treatment and shrend, carry out 180 ℃/6h peak value ageing treatment.At this moment, alloy tensile property and form of corrosion see Table 2.
Embodiment 9:
6082 aluminum alloy hot rolling sheet materials, through 560 ℃/1h solution treatment and air-cooled after, at first carry out 180 ℃/4h preageing, carry out afterwards draught and be 90% cold rolling at room temperature distortion, carry out at last again timeliness of 200 ℃/4h.At this moment, alloy tensile property and form of corrosion see Table 2.
Embodiment 10:
6082 aluminum alloy hot rolling sheet materials, through 550 ℃/1h solution treatment and air-cooled after, at first carry out 190 ℃/1h preageing, carry out afterwards draught and be 80% cold rolling at room temperature distortion, carry out at last again timeliness of 210 ℃/2h.At this moment, alloy tensile property and form of corrosion see Table 2.
Embodiment 11:
6082 aluminum alloy hot rolling sheet materials after 560 ℃/4h solution treatment and shrend, at first carry out 170 ℃/4h preageing, carry out afterwards draught and be 70% cold rolling at room temperature distortion, carry out at last again timeliness of 220 ℃/1h.At this moment, alloy tensile property and form of corrosion see Table 2.
Embodiment 12:
6082 aluminum alloy hot rolling sheet materials, through 530 ℃/4h solution treatment and air-cooled after, at first carry out 160 ℃/8h preageing, carry out afterwards draught and be 60% cold rolling at room temperature distortion, carry out at last again timeliness of 230 ℃/1h.At this moment, alloy tensile property and form of corrosion see Table 2.
Embodiment 13:
6082 aluminum alloy hot rolling sheet materials, through 550 ℃/1h solution treatment and air-cooled after, at first carry out 150 ℃/24h preageing, carry out afterwards draught and be 60% cold rolling at room temperature distortion, carry out at last again timeliness of 230 ℃/1h.At this moment, alloy tensile property and form of corrosion see Table 2.
Embodiment 14:
6082 aluminum alloy hot rolling sheet materials after 530 ℃/4h solution treatment and shrend, at first carry out 170 ℃/6h preageing, carry out afterwards draught and be 70% cold rolling at room temperature distortion, carry out at last again timeliness of 230 ℃/1h.At this moment, alloy tensile property and form of corrosion see Table 2.
Embodiment 15:
6082 aluminum alloy hot rolling sheet materials, through 550 ℃/1h solution treatment and air-cooled after, at first carry out 150 ℃/12h preageing, carry out afterwards draught and be 90% cold rolling at room temperature distortion, carry out at last again timeliness of 230 ℃/1h.At this moment, alloy tensile property and form of corrosion see Table 2.
Embodiment 16:
6082 aluminum alloy hot rolling sheet materials after 540 ℃/4h solution treatment and shrend, at first carry out 190 ℃/1h preageing, carry out afterwards draught and be 80% cold rolling at room temperature distortion, carry out at last again timeliness of 220 ℃/2h.At this moment, alloy tensile property and form of corrosion see Table 2.
Comparative example 3:
6056 aluminum alloy hot rolling sheet materials, through 530 ℃/4h solution treatment and air-cooled after, carry out 180 ℃/6h peak value ageing treatment, at this moment, alloy tensile property and form of corrosion see Table 3.
Embodiment 17:
6056 aluminum alloy hot rolling sheet materials, 530 ℃/4h solution treatment and air-cooled after, at first carry out 180 ℃/6h preageing, carry out afterwards draught and be 90% cold rolling at room temperature distortion, carry out at last again timeliness of 200 ℃/4h.At this moment, alloy tensile property and form of corrosion see Table 3.
Embodiment 18:
6056 aluminum alloy hot rolling sheet materials after 550 ℃/1h solution treatment and the shrend, at first carry out 190 ℃/1h preageing, carry out afterwards draught and be 80% cold rolling at room temperature distortion, carry out at last again timeliness of 170 ℃/8h.At this moment, alloy tensile property and form of corrosion see Table 3.
Embodiment 19:
6056 aluminum alloy hot rolling sheet materials after 550 ℃/4h solution treatment and the shrend, at first carry out 170 ℃/4h preageing, carry out afterwards draught and be 70% cold rolling at room temperature distortion, carry out at last again timeliness of 160 ℃/12h.At this moment, alloy tensile property and form of corrosion see Table 3.
Embodiment 20:
6056 aluminum alloy hot rolling sheet materials, 560 ℃/4h solution treatment and air-cooled after, at first carry out 180 ℃/4h preageing, carry out afterwards draught and be 60% cold rolling at room temperature distortion, carry out at last again timeliness of 230 ℃/1h.At this moment, alloy tensile property and form of corrosion see Table 3.
Embodiment 21:
6056 aluminum alloy hot rolling sheet materials, 550 ℃/1h solution treatment and air-cooled after, at first carry out 190 ℃/2h preageing, carry out afterwards draught and be 80% cold rolling at room temperature distortion, carry out at last again timeliness of 200 ℃/4h.At this moment, alloy tensile property and form of corrosion see Table 3.
Embodiment 22:
6056 aluminum alloy hot rolling sheet materials, through 540 ℃/4h solution treatment and air-cooled after, at first carry out 170 ℃/4h preageing, carry out afterwards draught and be 60% cold rolling at room temperature distortion, carry out at last again timeliness of 210 ℃/4h.At this moment, alloy tensile property and form of corrosion see Table 3.
Embodiment 23:
6056 aluminum alloy hot rolling sheet materials after 530 ℃/1h solution treatment and shrend, at first carry out 160 ℃/12h preageing, carry out afterwards draught and be 75% cold rolling at room temperature distortion, carry out at last again timeliness of 220 ℃/2h.At this moment, alloy tensile property and form of corrosion see Table 3.
Embodiment 24:
6056 aluminum alloy hot rolling sheet materials after 560 ℃/4h solution treatment and shrend, at first carry out 150 ℃/24h preageing, carry out afterwards draught and be 90% cold rolling at room temperature distortion, carry out at last again timeliness of 230 ℃/1h.At this moment, alloy tensile property and form of corrosion see Table 3.
Table 16061 aluminum alloy plate materials tensile property and form of corrosion
Table 26082 aluminum alloy plate materials tensile property and form of corrosion
Table 36056 aluminum alloy plate materials tensile property and form of corrosion
Need to prove, although the present invention has only selected 6061,6082 and 6,056 three kinds to carry out performance test, the precipitated phase type of different 6000 line aluminium alloys, the rule such as separate out, grow up are basic identical.Therefore, technical solution of the present invention also can be applied to other 6000 line aluminium alloys such as 6063,6013,6010.Using when of the present invention, as long as for heterogeneity 6000 line aluminium alloys, the thermomechanical treatment processing parameter suitably adjusted get final product.
Claims (7)
1. the deformation heat treatment method of a line aluminium alloy is characterized in that: step is for processing 6000 line aluminium alloys successively through following steps: (1) solution treatment; (2) quench; (3) preageing; (4) cold roller and deformed; (5) timeliness again.
2. the deformation heat treatment method of 6000 line aluminium alloys according to claim 1, it is characterized in that: the described solution treatment of step (1), solid solubility temperature are 530 ℃-560 ℃, and solution time is 1-4h.
3. the deformation heat treatment method of 6000 line aluminium alloys according to claim 1 is characterized in that: the described quenching of step (2), employing water-cooled or air-cooled Cooling Mode.
4. the deformation heat treatment method of 6000 line aluminium alloys according to claim 1, it is characterized in that: the described preageing of step (3), preageing temperature are 150 ℃-190 ℃, and the preageing time is 1-24h.
5. the deformation heat treatment method of 6000 line aluminium alloys according to claim 1 is characterized in that: the described cold roller and deformed least amount of deformation of step (4) is greater than 60%, maximum deformation quantity then will take guarantee when cold roller and deformed alloy not cracking as prerequisite.
6. the deformation heat treatment method of 6000 line aluminium alloys according to claim 5 is characterized in that: described deflection is determined according to the preageing hardenability: when the preageing hardenability is low, select the moderate finite deformation amount; When the preageing hardenability is higher, select than the small deformation amount.
7. the deformation heat treatment method of 6000 line aluminium alloys according to claim 1, it is characterized in that: the described again aging temp of step (5) is 160 ℃-230 ℃, and aging time is 1-12h again.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2013102430599A CN103305779A (en) | 2013-06-18 | 2013-06-18 | Thermomechanical treatment method of 6000-series aluminum alloy |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2013102430599A CN103305779A (en) | 2013-06-18 | 2013-06-18 | Thermomechanical treatment method of 6000-series aluminum alloy |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN103305779A true CN103305779A (en) | 2013-09-18 |
Family
ID=49131490
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2013102430599A Pending CN103305779A (en) | 2013-06-18 | 2013-06-18 | Thermomechanical treatment method of 6000-series aluminum alloy |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN103305779A (en) |
Cited By (20)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103510029A (en) * | 2013-09-23 | 2014-01-15 | 北京有色金属研究总院 | Solution heat treatment method suitable for 6000 series aluminum alloy automobile body plate |
| CN104060201A (en) * | 2014-06-17 | 2014-09-24 | 常州大学 | Thermomechanical treatment method capable of simultaneously improving strength and intercrystalline corrosion resistance of 6000 series aluminum alloy |
| CN104313521A (en) * | 2014-11-12 | 2015-01-28 | 西南铝业（集团）有限责任公司 | Machining method capable of improving performance of 7075 aluminum alloy plates |
| CN104625571A (en) * | 2015-01-06 | 2015-05-20 | 湖南科技大学 | Age-hardening aluminum alloy cutting method |
| CN105018804A (en) * | 2014-04-24 | 2015-11-04 | 贵州理工学院 | Al-Mg-Si as-cast aluminum alloy and aging treatment process thereof |
| CN105088112A (en) * | 2015-06-30 | 2015-11-25 | 黄河科技学院 | Heat treatment technology for 7-series high-strength aluminum alloy |
| CN105463350A (en) * | 2015-12-01 | 2016-04-06 | 国际铝业(厦门)有限公司 | Treatment process for increasing elongation of thick-wall aluminum alloy profile |
| CN106480384A (en) * | 2016-11-08 | 2017-03-08 | 广西科技大学 | A kind of milling method of ultrahigh-strength aluminum alloy sheet material |
| CN106637008A (en) * | 2016-11-08 | 2017-05-10 | 广西科技大学 | Rolling method for high-strength aluminum alloy plate |
| CN107723635A (en) * | 2017-11-06 | 2018-02-23 | 吉林大学 | A kind of processing method of high-strength aluminum alloy |
| CN108018509A (en) * | 2017-12-19 | 2018-05-11 | 重庆大学 | A kind of deformation heat treatment method for improving aluminum alloy rolled plate mechanical property |
| CN108588597A (en) * | 2018-05-09 | 2018-09-28 | 中南大学 | A kind of cycle heat treatment method improving aluminium alloy automobile plate baking vanish performance |
| CN109706412A (en) * | 2019-01-09 | 2019-05-03 | 中车青岛四方机车车辆股份有限公司 | A kind of high intensity Al-Zn-Mg system alloy and its preparation method and application |
| CN109735781A (en) * | 2019-03-15 | 2019-05-10 | 合肥工业大学 | A kind of heat treatment process of 6063 aluminium alloy |
| CN109844160A (en) * | 2016-10-20 | 2019-06-04 | 肯联铝业辛根有限责任公司 | The thermomechanical timeliness of 6XXX extrusion |
| CN112375999A (en) * | 2020-11-13 | 2021-02-19 | 贵州电网有限责任公司 | Thermomechanical treatment method for obtaining composite nanostructure in aluminum alloy material |
| CN113122786A (en) * | 2020-01-13 | 2021-07-16 | 晟通科技集团有限公司 | Anti-corrosion treatment method of paint-free aluminum alloy product |
| CN116121672A (en) * | 2023-02-21 | 2023-05-16 | 西北工业大学 | Method for thermo-mechanical treatment of aluminum alloy through compression-torsion composite deformation |
| CN116145056A (en) * | 2023-02-21 | 2023-05-23 | 西北工业大学 | Forming method of aluminum alloy disc parts |
| CN116145056B (en) * | 2023-02-21 | 2024-06-25 | 西北工业大学 | Forming method of aluminum alloy disc parts |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2000054052A (en) * | 1998-08-10 | 2000-02-22 | Honda Motor Co Ltd | High strength 6000 series aluminum alloy excellent in stress corrosion cracking resistance and heat treatment |
| US20070209739A1 (en) * | 2003-12-11 | 2007-09-13 | Nippon Light Metal Company, Ltd. | Method for producing Al-Mg-Si alloy sheet excellent in bake-hardenability and hemmability |
| CN102242325A (en) * | 2011-07-12 | 2011-11-16 | 中南大学 | Heat treatment technology for markedly raising comprehensive performance of aluminium alloy |
-
2013
- 2013-06-18 CN CN2013102430599A patent/CN103305779A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2000054052A (en) * | 1998-08-10 | 2000-02-22 | Honda Motor Co Ltd | High strength 6000 series aluminum alloy excellent in stress corrosion cracking resistance and heat treatment |
| US20070209739A1 (en) * | 2003-12-11 | 2007-09-13 | Nippon Light Metal Company, Ltd. | Method for producing Al-Mg-Si alloy sheet excellent in bake-hardenability and hemmability |
| CN102242325A (en) * | 2011-07-12 | 2011-11-16 | 中南大学 | Heat treatment technology for markedly raising comprehensive performance of aluminium alloy |
Cited By (24)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103510029B (en) * | 2013-09-23 | 2016-08-10 | 北京有色金属研究总院 | A kind of solid solution heat treatment method being applicable to 6000 line aluminium alloy car body panel |
| CN103510029A (en) * | 2013-09-23 | 2014-01-15 | 北京有色金属研究总院 | Solution heat treatment method suitable for 6000 series aluminum alloy automobile body plate |
| CN105018804A (en) * | 2014-04-24 | 2015-11-04 | 贵州理工学院 | Al-Mg-Si as-cast aluminum alloy and aging treatment process thereof |
| CN104060201A (en) * | 2014-06-17 | 2014-09-24 | 常州大学 | Thermomechanical treatment method capable of simultaneously improving strength and intercrystalline corrosion resistance of 6000 series aluminum alloy |
| CN104060201B (en) * | 2014-06-17 | 2016-06-29 | 常州大学 | A kind of deformation heat treatment method simultaneously improving 6000 line aluminium alloy intensity and intercrystalline corrosion drag |
| CN104313521A (en) * | 2014-11-12 | 2015-01-28 | 西南铝业（集团）有限责任公司 | Machining method capable of improving performance of 7075 aluminum alloy plates |
| CN104625571A (en) * | 2015-01-06 | 2015-05-20 | 湖南科技大学 | Age-hardening aluminum alloy cutting method |
| CN105088112A (en) * | 2015-06-30 | 2015-11-25 | 黄河科技学院 | Heat treatment technology for 7-series high-strength aluminum alloy |
| CN105463350A (en) * | 2015-12-01 | 2016-04-06 | 国际铝业(厦门)有限公司 | Treatment process for increasing elongation of thick-wall aluminum alloy profile |
| CN109844160A (en) * | 2016-10-20 | 2019-06-04 | 肯联铝业辛根有限责任公司 | The thermomechanical timeliness of 6XXX extrusion |
| CN106480384A (en) * | 2016-11-08 | 2017-03-08 | 广西科技大学 | A kind of milling method of ultrahigh-strength aluminum alloy sheet material |
| CN106637008A (en) * | 2016-11-08 | 2017-05-10 | 广西科技大学 | Rolling method for high-strength aluminum alloy plate |
| CN106480384B (en) * | 2016-11-08 | 2018-01-23 | 广西科技大学 | A kind of milling method of ultrahigh-strength aluminum alloy sheet material |
| CN107723635A (en) * | 2017-11-06 | 2018-02-23 | 吉林大学 | A kind of processing method of high-strength aluminum alloy |
| CN108018509A (en) * | 2017-12-19 | 2018-05-11 | 重庆大学 | A kind of deformation heat treatment method for improving aluminum alloy rolled plate mechanical property |
| CN108588597A (en) * | 2018-05-09 | 2018-09-28 | 中南大学 | A kind of cycle heat treatment method improving aluminium alloy automobile plate baking vanish performance |
| CN108588597B (en) * | 2018-05-09 | 2019-09-17 | 中南大学 | A kind of cycle heat treatment method improving aluminium alloy automobile plate baking vanish performance |
| CN109706412A (en) * | 2019-01-09 | 2019-05-03 | 中车青岛四方机车车辆股份有限公司 | A kind of high intensity Al-Zn-Mg system alloy and its preparation method and application |
| CN109735781A (en) * | 2019-03-15 | 2019-05-10 | 合肥工业大学 | A kind of heat treatment process of 6063 aluminium alloy |
| CN113122786A (en) * | 2020-01-13 | 2021-07-16 | 晟通科技集团有限公司 | Anti-corrosion treatment method of paint-free aluminum alloy product |
| CN112375999A (en) * | 2020-11-13 | 2021-02-19 | 贵州电网有限责任公司 | Thermomechanical treatment method for obtaining composite nanostructure in aluminum alloy material |
| CN116121672A (en) * | 2023-02-21 | 2023-05-16 | 西北工业大学 | Method for thermo-mechanical treatment of aluminum alloy through compression-torsion composite deformation |
| CN116145056A (en) * | 2023-02-21 | 2023-05-23 | 西北工业大学 | Forming method of aluminum alloy disc parts |
| CN116145056B (en) * | 2023-02-21 | 2024-06-25 | 西北工业大学 | Forming method of aluminum alloy disc parts |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103305779A (en) | Thermomechanical treatment method of 6000-series aluminum alloy | |
| CN100351415C (en) | Ferritic stainless steel sheet with excellent formability, and its manufacturing method | |
| CN105088118B (en) | A kind of ultra-fine crystallization method of nickel-based high-temperature alloy sheet material | |
| CN104046917B (en) | Superhigh intensity ferritic steel and the manufacture method thereof of rich Cu nanocluster strengthening | |
| CN112063883B (en) | Aluminum bronze and preparation method thereof | |
| US10260137B2 (en) | Method for producing Ni-based superalloy material | |
| US10344367B2 (en) | Method for producing Ni-based superalloy material | |
| CN113584343B (en) | Corrosion-resistant high-manganese aluminum bronze alloy and preparation method thereof | |
| JP2009041045A (en) | Aluminum alloy sheet having superior paint-baking hardenability and manufacturing method therefor | |
| CN103343304B (en) | The deformation heat treatment method of a kind of raising 6000 line aluminium alloy Sheet stretch performances | |
| CN112962033B (en) | High-strength invar alloy and processing method thereof | |
| CN110423966A (en) | A kind of preparation process improving aluminium lithium alloy product comprehensive performance | |
| JP2006257522A (en) | Al-Zn-Mg-Cu-BASED ALUMINUM ALLOY CONTAINING ZR AND METHOD FOR MANUFACTURING THE SAME | |
| CN111974919A (en) | Forging method for improving anisotropy of 7XXX aluminum alloy forging | |
| CN114214532B (en) | Method for realizing gamma-TiAl alloy refinement by accurately controlling metastable structure stabilization | |
| CN105568113A (en) | Composite strengthening and toughening technology of high-tensile Fe-Ni-Cr-based high-temperature corrosion-resisting alloy | |
| EP3505648B1 (en) | High-strength aluminum alloy, internal combustion engine piston comprising said alloy, and method for producing internal combustion engine piston | |
| CN103958711A (en) | Plate-like conductor for bus bar, and bus bar comprising same | |
| CN103834885A (en) | Thermal treatment method for improving plasticity of aluminum alloy plate material | |
| JP2010248607A (en) | Aluminum alloy sheet having excellent formability | |
| CN106367700B (en) | Eutectic Silicon in Al-Si Cast Alloys nodularization heat treatment method in a kind of cocrystallized Al-Si alloy | |
| CN112921208A (en) | Preparation method of Al-Mg-Si series aluminum alloy plate with high forming performance | |
| CN104532091A (en) | 2-series aluminum alloy | |
| CN105200283A (en) | New process avoiding coarse 6063 extrusion aluminum alloy crystals | |
| CN105112744A (en) | Manufacturing process of high-silicon aluminum alloy plate |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C12 | Rejection of a patent application after its publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20130918 |