CN105603340B - Improve the processing technology of the 2 antifatigue damage performances of ××× line aluminium alloy sheet material - Google Patents
Improve the processing technology of the 2 antifatigue damage performances of ××× line aluminium alloy sheet material Download PDFInfo
- Publication number
- CN105603340B CN105603340B CN201610018141.5A CN201610018141A CN105603340B CN 105603340 B CN105603340 B CN 105603340B CN 201610018141 A CN201610018141 A CN 201610018141A CN 105603340 B CN105603340 B CN 105603340B
- Authority
- CN
- China
- Prior art keywords
- sheet material
- aluminium alloy
- line aluminium
- finished product
- processing technology
- 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.)
- Active
Links
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
Abstract
The present invention relates to a kind of processing technology for improving the 2 antifatigue damage performances of ××× line aluminium alloy sheet material, comprise the following steps：（1）Dispensing melting is carried out to alloy and is cast as ingot casting；（2）Ingot casting is subjected to Homogenization Treatments, milling face and alclad successively, preheats, hot roughing plate is made；（3）By hot roughing plate hot finishing, cold-rolling deformation to finished product sheet metal thickness；（4）Reply pre-anneal treatment is carried out, the temperature for replying preannealing is 250~320 DEG C, and soaking time is 2~20h；（5）Solution hardening processing is carried out, solid solubility temperature is 480~505 DEG C, and soaking time is 3~60min；（6）Sheet material is aligned, and natrual ageing is to stable state.The present invention replys pre-anneal treatment by increasing, and can effectively control sheet material L ST section crystal grain average equivalent diameters and crystal grain length-width ratio, the tensile mechanical properties of sheet material and fatigue crack growth rate is satisfied by the requirement of the air standards of AMS 4296.
Description
Technical field
The present invention is a kind of processing technology for improving the 2 antifatigue damage performances of ××× line aluminium alloy sheet material, belongs to coloured
Metal material engineering field.
Background technology
With the development of aircraft industry, higher requirement is proposed to material, the aluminum alloy plate materials as aircraft skin are not
Only to meet intensity requirement, and require the features such as security, reliability and long lifespan.This requires aircraft aluminium alloy
Skin material takes into account high-fracture toughness and the performance requirement of antifatigue damage while intensity is met.
Nineteen ninety-five, Alcoa developed 2524 aluminium alloys for aircraft skin, and in the air standards of AMS 4296
Middle regulation：For thickness >=1.57mm 2524-T3 sheet materials, its yield strength, tensile strength and elongation percentage are not less than respectively
276MPa, 421Mpa and 15%；For thickness<1.57mm 2524-T3 sheet materials, its yield strength, tensile strength and elongation percentage
It is not less than 269MPa, 407Mpa and 15% respectively.Work as R=0.1, when loading frequency f=2~10HZ, Δ K=33MPa √ m,
2524-T3 aluminum alloy plate materials fatigue crack growth rate da/dN=3.05 × 10 that highest is allowed in actual applications-3mm/
cycle。
In recent years, both at home and abroad on sheet material fatigue crack growth rate influence factor research and improve sheet material fatigue crack
The method of spreading rate, it is concentrated mainly on optimized alloy composition and the control phase of sheet material second.Such as patent US7323068B2,
Mainly by limiting Fe, Si impurity content in 2024 aluminium alloys, add Zr and reduce Mn contents to improve the comprehensive of alloy
Performance is closed, alloying component is：Cu3.8-4.7%, Mg1.0-1.6%, Zr0.06-0.18%, Cr<0.15%, Mn>0-
0.50%, Fe≤0.15%, Si≤0.15%.Patent US5213639A, by controlling the content of main alloying element to improve alloy
Fracture toughness and resistance to crack extension performance, alloying component be：Cu4-4.5%, Mg1.2-1.5%, Mn0.4-0.6%, Fe≤
0.12%, Si≤0.1%.Document《The Formative Mechanism of 2024-T3 and 2524-T3 aluminum alloy fatigue crackles》Research shows：2524
The most crackle of aluminium alloy germinates all at second phase particles, and belt area more in second phase particles, thick by second
Ftractureed at the second phase particles ruptured in phase particle or hot rolling.And on grain morphology and size to sheet material crack Propagation speed
The influence research of rate and the report of regulation and control sheet material grain morphology and measures are less.
The content of the invention
The invention provides a kind of processing technology for improving the 2 antifatigue damage performances of ××× line aluminium alloy sheet material, pass through
Pre-anneal treatment is replied in increase, to control sheet material L-ST sections crystal grain average equivalent diameter and crystal grain length-width ratio in required scope
It is interior, the tensile mechanical properties of sheet material and fatigue crack growth rate is satisfied by the air standards of AMS 4296.
The technical scheme is that：A kind of processing work for improving the 2 antifatigue damage performances of ××× line aluminium alloy sheet material
Skill, comprise the following steps：
(1) dispensing melting is carried out according to 2 ××× line aluminium alloy compositions and its content range, casting obtains required ingot casting；
(2) ingot casting is subjected to Homogenization Treatments, milling face and alclad successively, carries out preheating and hot roughing again afterwards, heat is made
Roughing plate；
(3) by hot roughing plate hot finishing, cold-rolling deformation to finished product sheet metal thickness；
(4) sheet material for being rolled to finished product sheet metal thickness is subjected to reply pre-anneal treatment, reply the temperature of preannealing for 250~
320 DEG C, soaking time is 2~20h；
(5) solution hardening processing will be carried out through replying the sheet material of pre-anneal treatment, solid solubility temperature is 480~505 DEG C, insulation
Time is 3~60min；
(6) sheet material after solution hardening is aligned, and natrual ageing is to stable state.
Further, the processing technology of the above-mentioned antifatigue damage performance of ××× line aluminium alloy sheet material of raising 2, wherein：Institute
State in step (3) for plate product, its finished product sheet metal thickness >=4.0mm, be preferably >=5.0mm, pass through hot finishing to finished product
Sheet metal thickness；For cut deal product, its finished product sheet metal thickness is 2.0~6.0mm, preferably 2.5~5.0mm, passes through hot essence
After rolling finished product sheet metal thickness is deformed into through cold finish to gauge；For light sheet products, its finished product sheet metal thickness<2.5mm, be preferably≤
2.0mm, by being deformed into finished product sheet metal thickness through cold rolling, intermediate annealing and cold finish to gauge after hot finishing.
Further, the processing technology of the above-mentioned antifatigue damage performance of ××× line aluminium alloy sheet material of raising 2, wherein：Institute
State in step (3), for cut deal and light sheet products, cold finish to gauge reduction ratio preferably 40~75%.
Further, the processing technology of the above-mentioned antifatigue damage performance of ××× line aluminium alloy sheet material of raising 2, wherein：It is right
In light sheet products, cold rolling intermediate anneal temperature is 250~450 DEG C, preferably 300~400 DEG C, is incubated 2~20h.
Further, the processing technology of the above-mentioned antifatigue damage performance of ××× line aluminium alloy sheet material of raising 2, wherein：
For light sheet products, cold rolling and intermediate annealing process are selectively repeatedly.
Further, the processing technology of the above-mentioned antifatigue damage performance of ××× line aluminium alloy sheet material of raising 2, wherein：
Alloy material composition in the step (1) is the 2 ××× line aluminium alloys including AA2024, AA2524.
Further, the processing technology of the above-mentioned antifatigue damage performance of ××× line aluminium alloy sheet material of raising 2, wherein：
Preferably 270~300 DEG C of Pre-annealing Temperature, soaking time preferably 4~8h are replied in the step (4).
The substantive distinguishing features and significant technological progress of the present invention are embodied in：Preanneal process is replied by increasing, can be made
Between 30~150 μm, crystal grain length-width ratio controls between 2.5~7.0 the crystal grain average equivalent diameter control of sheet material L-ST sections；
Work as R=0.1, when loading frequency f=2~10HZ, Δ K=33MPa √ m, sheet material fatigue crack growth rate da/dN≤3.05 ×
10-3Mm/cycle, fatigue crack growth rate and tensile mechanical properties are satisfied by the requirement of the air standards of AMS 4296；In addition, this
Invention is widely used, and is not only applicable 2 ××× line aluminium alloy sheet materials of aircraft skin including AA2024, AA2524, its
It needs the aluminum alloy plate materials for improving antifatigue damage performance to be also prepared using this method.
Brief description of the drawings
Fig. 1 is the technological process for preparing 2 ×××-T3 aluminium alloy thick plates；
Fig. 2 is the technological process for preparing 2 ×××-T3 Aluminum Alloy Plates；
Fig. 3 is the technological process for preparing 2 ×××-T3 aluminium alloy sheets.
Fig. 4 is the metallographic microstructure of the 2524-T3 slab L-ST sections D/4 positions of embodiment 1.
Fig. 5 is the metallographic microstructure in the 2524-T3 cut deal L-ST sections of embodiment 2 and comparative example 1.
Fig. 6 is the metallographic microstructure in the 2524-T3 thin plate L-ST sections of embodiment 4 and comparative example 3.
Embodiment
Below in conjunction with accompanying drawing table, specific embodiment and comparative example, the embodiment of the present invention is described in further detail,
So that technical solution of the present invention is more readily understood and grasped.
A kind of processing technology of the antifatigue damage performance of ××× line aluminium alloy sheet material of raising 2 proposed by the invention, its
It is characterised by comprising the following steps：
(1) dispensing melting being carried out according to 2 ××× line aluminium alloy compositions and its content range, casting obtains required ingot casting,
Alloy material composition is the 2 ××× line aluminium alloys including AA2024, AA2524；
(2) ingot casting is subjected to Homogenization Treatments, milling face and alclad successively, carries out preheating and hot roughing again afterwards, heat is made
Roughing plate；
(3) by hot roughing plate hot finishing, cold-rolling deformation to finished product sheet metal thickness；It is thick for plate product, its finished product sheet material
Degree >=4.0mm, it is preferably >=5.0mm, passes through hot finishing to finished product sheet metal thickness；It is thick for cut deal product, its finished product sheet material
Spend for 2.0~6.0mm, preferably 2.5~5.0mm, by being deformed into finished product sheet metal thickness through cold finish to gauge after hot finishing；For thin
Panel products, its finished product sheet metal thickness<2.5mm, be preferably≤2.0mm, by after hot finishing through cold rolling, intermediate annealing and cold finish to gauge
It is deformed into finished product sheet metal thickness.
(4) sheet material for being rolled to finished product sheet metal thickness is subjected to reply pre-anneal treatment, reply the temperature of preannealing for 250~
320 DEG C, soaking time is 2~20h；
(5) solution hardening processing will be carried out through replying the sheet material of pre-anneal treatment, solid solubility temperature is 480~505 DEG C, insulation
Time is 3~60min；
(6) sheet material after solution hardening is aligned, and natrual ageing is to stable state.
In above-mentioned steps (3), for cut deal and light sheet products, cold finish to gauge reduction ratio preferably 40~75%.For thin plate
Product, cold rolling intermediate anneal temperature are 250~450 DEG C, preferably 300~400 DEG C, are incubated 2~20h.And for light sheet products,
Cold rolling and intermediate annealing process are selectively repeatedly.Preferably 270~300 DEG C of Pre-annealing Temperature is replied in the step (4),
Soaking time preferably 4~8h.
Embodiment 1
By 4.32wt.%Cu, 1.35wt.%Mg, 0.61wt.%Mn, 0.08wt.%Fe, 0.06wt.%Si,
The 0.03wt.%Ti aluminium alloy cast ingot of element proportioning 400 × 1620 × 2500mm of founding specifications 2524.Alloy cast ingot is entered successively
498 DEG C/32h of row Homogenization Treatments, milling face, alclad, 480 DEG C/8h preheatings, after 480 DEG C of hot roughing, and then hot finishing is extremely
6.0mm.By hot finishing plate in 290 DEG C be incubated 4h, after through 496 DEG C/50min solution hardening, straightening processing and natrual ageing 96h
More than, technological process is as shown in Figure 1.The tensile mechanical properties of final finished sheet material are tested, and press GB/T 6398-2000 and AMS
The fatigue crack growth rate of 4296 standard testing sheet materials.
Embodiment 2
By 4.32wt.%Cu, 1.35wt.%Mg, 0.61wt.%Mn, 0.08wt.%Fe, 0.06wt.%Si,
The 0.03wt.%Ti aluminium alloy cast ingot of element proportioning 400 × 1620 × 2500mm of founding specifications 2524.Ingot casting is carried out successively
498 DEG C/32h Homogenization Treatments, milling face, alclad, 480 DEG C/8h preheatings, afterwards in 480 DEG C of hot roughing, and then hot finishing is extremely
6.0mm.Hot finishing plate is deformed into 2.5mm by the cold finish to gauge of 58% reduction ratio, by cold finish to gauge plate in 270 DEG C be incubated 8h, after pass through
496 DEG C/25min solution hardening, but after straightening processing more than natrual ageing 96h, technological process is as shown in Figure 2.Test is final
The mechanical property of finished product sheet material, and by the crack Propagation speed of the standard testing sheet material of GB/T 6398-2000 and AMS 4296
Rate.
Embodiment 3
By 4.32wt.%Cu, 1.35wt.%Mg, 0.61wt.%Mn, 0.08wt.%Fe, 0.06wt.%Si,
The 0.03wt.%Ti aluminium alloy cast ingot of element proportioning 400 × 1620 × 2500mm of founding specifications 2524.Ingot casting is carried out successively
498 DEG C/32h Homogenization Treatments, milling face, alclad, 480 DEG C/8h preheatings, afterwards in 480 DEG C of hot roughing, and then hot finishing is extremely
6.0mm.Hot finishing plate is deformed into 2.5mm by the cold finish to gauge of 58% reduction ratio, by cold finish to gauge plate in 290 DEG C be incubated 4h, after pass through
496 DEG C/25min solution hardening, but after straightening processing more than natrual ageing 96h, technological process is as shown in Figure 2.Test is final
The mechanical property of finished product sheet material, and by the crack Propagation speed of the standard testing sheet material of GB/T 6398-2000 and AMS 4296
Rate.
Embodiment 4
By 4.28wt.%Cu, 1.30wt.%Mg, 0.60wt.%Mn, 0.08wt.%Fe, 0.06wt.%Si,
The 0.03wt.%Ti aluminium alloy cast ingot of element proportioning 400 × 1620 × 2500mm of founding specifications 2524.Ingot casting is carried out successively
498 DEG C/30h Homogenization Treatments, milling face, alclad, 485 DEG C/8h preheatings, hot roughing and hot finishing to 4.5mm.Hot finishing plate is pressed
56% reduction ratio cold-rolling deformation is deformed into 2.0mm, then through 340 DEG C/4h intermediate annealings and by the cold finish to gauge of 60% reduction ratio
0.8mm.Cold finish to gauge plate is incubated 8h in 275 DEG C, after through 498 DEG C/16min solution hardening, and it is natural after straightening processing when
More than 96h is imitated, technological process is as shown in Figure 3.Test the mechanical property of final finished sheet material, and by GB/T 6398-2000 and
The fatigue crack growth rate of the standard testing sheet materials of AMS 4296.
Embodiment 5
By 4.28wt.%Cu, 1.30wt.%Mg, 0.60wt.%Mn, 0.08wt.%Fe, 0.06wt.%Si,
The 0.03wt.%Ti aluminium alloy cast ingot of element proportioning 400 × 1620 × 2500mm of founding specifications 2524.Ingot casting is carried out successively
498 DEG C/30h Homogenization Treatments, milling face, alclad, 485 DEG C/8h preheatings, hot roughing and hot finishing to 4.5mm.Hot finishing plate is pressed
56% reduction ratio cold-rolling deformation is deformed into 2.0mm, then through 340 DEG C/4h intermediate annealings and by the cold finish to gauge of 60% reduction ratio
0.8mm.Cold finish to gauge plate is incubated 4h in 290 DEG C, after through 498 DEG C/16min solution hardening, and it is natural after straightening processing when
More than 96h is imitated, technological process is as shown in Figure 3.Test the mechanical property of final finished sheet material, and by GB/T 6398-2000 and
The fatigue crack growth rate of the standard testing sheet materials of AMS 4296.
Comparative example 1
By 4.32wt.%Cu, 1.35wt.%Mg, 0.61wt.%Mn, 0.08wt.%Fe, 0.06wt.%Si,
The 0.03wt.%Ti aluminium alloy cast ingot of element proportioning 400 × 1620 × 2500mm of founding specifications 2524.Ingot casting is carried out successively
498 DEG C/32h Homogenization Treatments, milling face, alclad, 480 DEG C/8h preheatings, after 480 DEG C of hot roughing, and then hot finishing is extremely
6.0mm.Hot finishing plate is deformed into 2.5mm by the cold finish to gauge of 58% reduction ratio, then directly through 496 DEG C/25min solution hardening,
Again after straightening processing more than natrual ageing 96h.Test the mechanical property of final finished sheet material, and by GB/T 6398-2000 and
The fatigue crack growth rate of the standard testing sheet materials of AMS 4296.
Comparative example 2
By 4.32wt.%Cu, 1.35wt.%Mg, 0.61wt.%Mn, 0.08wt.%Fe, 0.06wt.%Si,
The 0.03wt.%Ti aluminium alloy cast ingot of element proportioning 400 × 1620 × 2500mm of founding specifications 2524.Ingot casting is carried out successively
498 DEG C/32h Homogenization Treatments, milling face, alclad, 480 DEG C/8h preheatings, afterwards in 480 DEG C of hot roughing, and then hot finishing is extremely
6.0mm.Hot finishing plate is deformed into 2.5mm by the cold finish to gauge of 58% reduction ratio, by cold-reduced sheet in 200 DEG C be incubated 4h, after through 496
DEG C/25min solution hardening, but after straightening processing more than natrual ageing 96h, technological process is as shown in Figure 2.Test final finished
The mechanical property of sheet material, and by the fatigue crack growth rate of the standard testing sheet material of GB/T 6398-2000 and AMS 4296.
Comparative example 3
By 4.28wt.%Cu, 1.30wt.%Mg, 0.60wt.%Mn, 0.08wt.%Fe, 0.06wt.%Si,
The 0.03wt.%Ti aluminium alloy cast ingot of element proportioning 400 × 1620 × 2500mm of founding specifications 2524.Ingot casting is carried out successively
498 DEG C/30h Homogenization Treatments, milling face, alclad, 485 DEG C/8h preheatings, afterwards in 485 DEG C of hot roughing, and then hot finishing is extremely
4.5mm.By hot finishing plate by 56% reduction ratio cold-rolling deformation to 2.0mm, then through 340 DEG C/4h intermediate annealings and by 60% pressure
The cold finish to gauge of rate is deformed into 0.8mm.By cold-reduced sheet directly through 498 DEG C/16min solution hardening, and the natrual ageing after straightening processing
More than 96h.The mechanical property of final finished sheet material is tested, and by the standard testing sheet material of GB/T 6398-2000 and AMS 4296
Fatigue crack growth rate.
Comparative example 4
By 4.28wt.%Cu, 1.30wt.%Mg, 0.60wt.%Mn, 0.08wt.%Fe, 0.06wt.%Si,
The 0.03wt.%Ti aluminium alloy cast ingot of element proportioning 400 × 1620 × 2500mm of founding specifications 2524.Ingot casting is carried out successively
498 DEG C/30h Homogenization Treatments, milling face, alclad, 485 DEG C/8h preheatings, hot roughing and hot finishing to 4.5mm.Hot finishing plate is pressed
56% reduction ratio cold-rolling deformation is deformed into 2.0mm, then through 340 DEG C/4h intermediate annealings and by the cold finish to gauge of 60% reduction ratio
0.8mm.Cold finish to gauge plate is incubated 4h in 225 DEG C, after through 498 DEG C/16min solution hardening, and it is natural after straightening processing when
More than 96h is imitated, technological process is as shown in Figure 3.Test the mechanical property of final finished sheet material, and by GB/T 6398-2000 and
The fatigue crack growth rate of the standard testing sheet materials of AMS 4296.
Table 1 is the technological parameter that 2524-T3 aluminum alloy plate materials are produced in embodiment and comparative example, and table 2 gives embodiment
With the fatigue crack prop- agation speed of 2524-T3 aluminium alloys finished product sheet material in comparative example.
From table 1 it follows that experienced reply preannealing before plate solution hardening is rolled in embodiment, and reply and move back in advance
The time long enough of fire；And in comparative example, without replying pre-anneal treatment, comparative example before comparative example 1 and the solution hardening of comparative example 3
It is although shorter through reply pre-anneal treatment, soaking time before 2 and the solution hardening of comparative example 4.
From Table 2, it can be seen that the crystal grain average equivalent diameter of the 2524-T3 sheet materials of embodiment 1,2,3,4 and 5 is all higher than
30 μm, length-width ratio is also greater than 2.5.Fig. 4 is the production board metallographic overlay film photo of embodiment 1, and sheet material crystal grain average equivalent is straight in figure
Footpath is 70 μm, length-width ratio 6.5.The fatigue crack growth rate da/dN ＜ 3.05 × 10 of acetonideexample 2524-T3 sheet materials- 3Mm/cycle, fatigue crack growth rate and mechanical property are satisfied by the requirement of the air standards of AMS 4296.And comparative example 1,2,3
It is less than 30 μm with 4 2524-T3 sheet materials grain size or length-width ratio is less than 2.5, although mechanical property meets AMS 4296
Air standard requirement, but fatigue crack growth rate da/dN ＞ 3.05 × 10-3Mm/cycle, it is unsatisfactory for the aerial photogrammetric targets of AMS 4296
Alignment request.Comparative example 2 and comparative example 1 and embodiment 4 and comparative example 3, due to having carried out reply pre-anneal treatment before solid solution,
All big, Fig. 5 (a), Fig. 5 (b) difference of the crystallite dimension and length-width ratio of embodiment 2 and embodiment 4 than comparative example 1 and comparative example 3
Corresponding embodiment 2 and comparative example 1, Fig. 6 (a), Fig. 6 (b) correspond to embodiment 4 and comparative example 3 respectively.Comparative example 2,3 with than
Compared with example 2 and embodiment 4,5 and comparative example 4, the crystallite dimension and length-width ratio of embodiment are all higher than comparative example, before explanation should make solid solution
Preannealing holding time long is replied, could effectively increase production board crystallite dimension and length-width ratio.As can be seen here, using this hair
Preanneal process is replied in bright control, can effectively regulate and control the crystallite dimension and pattern of 2524-T3 sheet materials, so as to significantly drop
Low 2 ×××-T3 sheet materials fatigue crack growth rate da/dN values.
Certainly, it the above is only the concrete application example of the present invention, protection scope of the present invention be not limited in any way.It is all
The technical scheme formed using equivalent transformation or equivalent replacement, all fall within rights protection scope of the present invention.
Table 1 is the technological parameter for preparing 2524-T3 aluminum alloy plate materials
Table 2 is the tissue and the performance test results of the 2524-T3 sheet materials prepared by the technique of table 1
Note：Grain size is crystal grain homalographic diameter of a circle, and crystal grain average area=crystal grain major axis (L) is long average
Value × crystal grain short axle (S) long average value.The long axial length average value of the length-width ratio=crystal grain/long average value of crystal grain short axle.
Claims (6)
1. improve the processing technology of the 2 antifatigue damage performances of ××× line aluminium alloy sheet material, it is characterised in that comprise the following steps：
（1）Dispensing melting is carried out according to 2 ××× line aluminium alloy compositions and its content range, casting obtains required ingot casting；
（2）Ingot casting is subjected to Homogenization Treatments, milling face and alclad successively, preheating and hot roughing is carried out again afterwards, hot roughing is made
Plate；
（3）By hot roughing plate hot finishing, cold-rolling deformation to finished product sheet metal thickness；
（4）The sheet material for being rolled to finished product sheet metal thickness is subjected to reply pre-anneal treatment, the temperature for replying preannealing is 250~320
DEG C, soaking time is 2~20h；
（5）Solution hardening processing will be carried out through replying the sheet material of pre-anneal treatment, solid solubility temperature is 480~505 DEG C, soaking time
For 3~60min；
（6）Sheet material after solution hardening is aligned, and natrual ageing is to stable state；The step（3）In, for middle thickness
Plate and light sheet products, cold finish to gauge reduction ratio are 40~75%.
2. the processing technology according to claim 1 for improving the 2 antifatigue damage performances of ××× line aluminium alloy sheet material, it is special
Sign is：The step（3）In for plate product, its finished product sheet metal thickness >=4.0mm, it is thick to finished product sheet material to pass through hot finishing
Degree；For cut deal product, its finished product sheet metal thickness is 2.0~6.0mm, by being deformed into production board through cold finish to gauge after hot finishing
Material thickness；For light sheet products, its finished product sheet metal thickness<2.5mm, by after hot finishing through cold rolling, intermediate annealing and cold finish to gauge
It is deformed into finished product sheet metal thickness.
3. the processing technology according to claim 2 for improving the 2 antifatigue damage performances of ××× line aluminium alloy sheet material, it is special
Sign is：For light sheet products, cold rolling intermediate anneal temperature is 250~450 DEG C, is incubated 2~20h.
4. the processing technology according to claim 2 for improving the 2 antifatigue damage performances of ××× line aluminium alloy sheet material, it is special
Sign is：For light sheet products, cold rolling and intermediate annealing process are selectively repeatedly.
5. the processing technology according to claim 1 for improving the 2 antifatigue damage performances of ××× line aluminium alloy sheet material, it is special
Sign is：The step（1）In alloy material composition be 2 ××× line aluminium alloys including AA2024, AA2524.
6. the processing technology according to claim 1 for improving the 2 antifatigue damage performances of ××× line aluminium alloy sheet material, it is special
Sign is：The step（4）Middle reply Pre-annealing Temperature is 270~300 DEG C, and soaking time is 4~8h.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610018141.5A CN105603340B (en) | 2016-01-12 | 2016-01-12 | Improve the processing technology of the 2 antifatigue damage performances of ××× line aluminium alloy sheet material |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610018141.5A CN105603340B (en) | 2016-01-12 | 2016-01-12 | Improve the processing technology of the 2 antifatigue damage performances of ××× line aluminium alloy sheet material |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105603340A CN105603340A (en) | 2016-05-25 |
| CN105603340B true CN105603340B (en) | 2018-01-23 |
Family
ID=55983674
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610018141.5A Active CN105603340B (en) | 2016-01-12 | 2016-01-12 | Improve the processing technology of the 2 antifatigue damage performances of ××× line aluminium alloy sheet material |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105603340B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110565095A (en) * | 2019-09-25 | 2019-12-13 | 华为技术有限公司 | Workpiece of electronic equipment, preparation method, shell and electronic equipment |
| CN113201641B (en) * | 2021-04-26 | 2022-11-01 | 瑞安市创博机械有限公司 | Heat treatment method and heat treatment method for stretched aluminum guide roller |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101967615B (en) * | 2010-10-27 | 2012-06-27 | 中国航空工业集团公司北京航空材料研究院 | Method for improving damage-tolerance property of 2,000-type aluminium alloy plate material |
| CN103045976B (en) * | 2012-12-27 | 2014-11-05 | 中南大学 | Heat treatment method capable of improving anti-fatigue performance of aluminum alloy |
| CN103589977B (en) * | 2013-11-11 | 2015-11-18 | 中南大学 | A kind of method improving Al-Cu-Mg alloy anti-fatigue performance |
-
2016
- 2016-01-12 CN CN201610018141.5A patent/CN105603340B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN105603340A (en) | 2016-05-25 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN105483579B (en) | Improve the processing technology of the 2 antifatigue damage performances of ××× line aluminium alloy plank | |
| CN106591650B (en) | A method of improving aluminium lithium alloy anti-stress corrosion performance | |
| CN104711463B (en) | A kind of Al-Mg-Zn-Li alloy and sheet material preparation method thereof | |
| El-Sabbagh et al. | Hot rolling behaviour of stir-cast Al 6061 and Al 6082 alloys–SiC fine particulates reinforced composites | |
| CN103981410B (en) | A kind of high damnification resistant aluminum alloy and preparation method thereof | |
| CN105839039B (en) | A kind of preparation method of the TiAl alloy sheet material of uniform formation | |
| CN105441839B (en) | Improve the processing technology of the 2 antifatigue damage performances of ××× line aluminium alloy sheet material | |
| CN109988948B (en) | 5182-O state aluminum alloy plate for automobile inner plate and production method thereof | |
| KR102224687B1 (en) | Rolling and preparation method of magnesium alloy sheet | |
| JP5527498B2 (en) | Magnesium alloy plate excellent in room temperature formability and processing method of magnesium alloy plate | |
| CN107312986A (en) | A kind of preparation method of high-strength plasticity duplex grain structure almag | |
| RU2555267C2 (en) | Method of fabrication of thin sheets from two-phase titanium alloy and product from these sheets | |
| CN111069499B (en) | Forging process method for TC18 titanium alloy large-scale binding support forge piece | |
| CN109628803B (en) | Aluminum alloy checkered plate in 4017-H2X state and preparation method thereof | |
| CN105603340B (en) | Improve the processing technology of the 2 antifatigue damage performances of ××× line aluminium alloy sheet material | |
| CN106661678B (en) | Alloy and preparation method thereof for height moulding aluminium product | |
| CN105463349B (en) | Improve the heat treatment method of 2 ×××-T3 plate fatigue crack growth rates | |
| CN110684937B (en) | Preparation method of layered double-scale magnesium alloy | |
| RU2465973C1 (en) | Method of making foil from titanium-based intermetallide orthoalloys | |
| CN110093543B (en) | Goss + Cube or P + Cube texture aluminum alloy with excellent fracture toughness and preparation method thereof | |
| Shen et al. | Achieving high strain rate superplasticity in an Al-Cu-Li alloy processed by thermo-mechanical processing | |
| US6565683B1 (en) | Method for processing billets from multiphase alloys and the article | |
| CN112553485A (en) | Preparation process of high-formability 5754 aluminum alloy plate | |
| CN109487102B (en) | Preparation method of aluminum-magnesium-scandium alloy plate for superplastic forming | |
| CN115971249A (en) | Preparation method of ultrathin TC4 titanium 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 | ||
| TA01 | Transfer of patent application right |
Effective date of registration: 20171122 Address after: 102209 Changping District City, Beiqijia, the future of science and technology in the south area of the town of Beijing Applicant after: China Aluminum Material Applied Research Institute Co Ltd Applicant after: Southwest Aluminum (Group) Co., Ltd. Address before: 215026 Jiangsu Province, Suzhou City Industrial Park, No. 200 East Shen Hu Lu Applicant before: Suzhou Non-ferrous Metal academy Co., Ltd. Applicant before: CHINALCO INSTITUTE OF SCIENCE AND TECHNOLOGY CO., LTD. Applicant before: Southwest Aluminum (Group) Co., Ltd. |
|
| TA01 | Transfer of patent application right | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |