CN105603340A - Processing technique for improving fatigue damage resistance of 2XXX series aluminum alloy plate - Google Patents
Processing technique for improving fatigue damage resistance of 2XXX series aluminum alloy plate Download PDFInfo
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- CN105603340A CN105603340A CN201610018141.5A CN201610018141A CN105603340A CN 105603340 A CN105603340 A CN 105603340A CN 201610018141 A CN201610018141 A CN 201610018141A CN 105603340 A CN105603340 A CN 105603340A
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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
- C22F1/057—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 invention relates a processing technique for improving fatigue damage resistance of a 2XXX series aluminum alloy plate, comprising the following steps: (1), burdening and smelting an alloy, and casting to obtain an ingot; (2), subjecting the ingot sequentially to homogenizing, surface milling and aluminum cladding, and preheating to obtain a hot roughed plate; (3), subjecting the hot roughed plate to hot finishing and cold rolling deformation to finished plate thickness; (4), carrying out recovery pre-annealing at 250-320 DEG C, and holding the temperature for 2-20 h; (5), carrying out solid solution quenching at 480-505 DEG C, and holding the temperature for 3-60 min; (6), straightening a plate, and naturally ageing to a stable state. By adding the recovery pre-annealing treatment, it is possible to effectively control grain average equivalent diameter and grain length-width ratio of L-ST section of the plate, so that both tensile mechanical property of the plate and fatigue crack growth rate thereof meet the requirements of AMS 4296 aviation standards.
Description
Technical field
The present invention is a kind of processing technology that improves 2 × × × line aluminium alloy sheet material antifatigue damage performance, belongs to nonferrous materialsEngineering field.
Background technology
Along with the development of aircraft industry, material is had higher requirement, not only to expire as the aluminum alloy plate materials of aircraft skinFoot requirement of strength, and requirement has the features such as security, reliability and life-span length. This just requires aircraft aluminum alloy outer cover materialMaterial, in meeting intensity, is taken into account the performance requirement of high-fracture toughness and antifatigue damage.
Nineteen ninety-five, Alcoa developed 2524 aluminium alloys for aircraft skin, and in AMS4296 air standardRegulation: for the 2524-T3 sheet material of thickness >=1.57mm, its yield strength, tensile strength and percentage elongation are not less than respectively276MPa, 421Mpa and 15%; For the 2524-T3 sheet material of thickness < 1.57mm, its yield strength, tensile strength and prolongThe rate of stretching is not less than respectively 269MPa, 407Mpa and 15%. Work as R=0.1, loading frequency f=2～10HZ, Δ K=33MPa √ mTime, 2524-T3 aluminum alloy plate materials is the highest allowed fatigue crack growth rate da/dN=3.05 × 10 in actual applications- 3mm/cycle。
In recent years, the domestic and international research about sheet material fatigue crack growth rate influence factor and raising sheet material crack Propagation speedThe method of rate, mainly concentrates on optimized alloy composition and controls on sheet material second-phase. For example patent US7323068B2, mainBy limiting Fe, the Si impurity content in 2024 aluminium alloys, add Zr and reduce Mn content and carry heavy alloyed combiningClose performance, 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, puies forward heavy alloyed fracture toughness by the content of controlling main alloying elementWith resistance to crack extension performance, alloying component is: Cu4-4.5%, and Mg1.2-1.5%, Mn0.4-0.6%, Fe≤0.12%,Si≤0.1%. Document " Formative Mechanism of 2024-T3 and 2524-T3 aluminium alloy fatigue crack " research shows: 2524 aluminium alloysMost crackle is all in second phase particles place germinating, and how at the belt area of second phase particles, thick second phase particles orThe second phase particles place cracking breaking in hot rolling. And about grain morphology and size, the impact of sheet material fatigue crack growth rate is groundStudy carefully and to regulate and control the report of sheet material grain morphology and size method less.
Summary of the invention
The invention provides a kind of processing technology that improves 2 × × × line aluminium alloy sheet material antifatigue damage performance, reply by increasePreannealing processing, controls the average equivalent diameter of sheet material L-ST cross section crystal grain and crystal grain length-width ratio within the required range, makes sheet materialTensile mechanical properties and fatigue crack growth rate all meet AMS4296 air standard.
Technical scheme of the present invention is: a kind of processing technology that improves 2 × × × line aluminium alloy sheet material antifatigue damage performance, comprisesFollowing steps:
(1), according to the melting of preparing burden of 2 × × × line aluminium alloy composition and content range thereof, casting obtains required ingot casting;
(2) ingot casting is carried out to homogenising processing, milling face and alclad successively, carry out again afterwards preheating and hot roughing, make heat thickRoll plate;
(3) by hot roughing plate hot finishing, cold roller and deformed to finished product sheet metal thickness;
(4) sheet material that is rolled to finished product sheet metal thickness is replied to preannealing processing, reply the temperature of preannealing and be 250～320 DEG C, temperature retention time is 2～20h;
(5) will carry out solution hardening processing through the sheet material of replying preannealing processing, solid solubility temperature is 480～505 DEG C, when insulationBetween be 3～60min;
(6) sheet material after solution hardening is aligned, and natrual ageing is to stable state.
Further, the processing technology of above-mentioned raising 2 × × × line aluminium alloy sheet material antifatigue damage performance, wherein: described step(3) in, for slab product, its finished product sheet metal thickness >=4.0mm, is preferably >=5.0mm, by hot finishing to finished product sheet materialThickness; For cut deal product, its finished product sheet metal thickness is 2.0～6.0mm, is preferably 2.5～5.0mm, by hot finishingBe deformed into finished product sheet metal thickness by cold finish to gauge; For light sheet products, its finished product sheet metal thickness < 2.5mm, is 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 above-mentioned raising 2 × × × line aluminium alloy sheet material antifatigue damage performance, wherein: described step(3) in, for cut deal and light sheet products, cold finish to gauge reduction ratio preferably 40～75%.
Further, the processing technology of above-mentioned raising 2 × × × line aluminium alloy sheet material antifatigue damage performance, wherein: for thin plateProduct, cold rolling intermediate annealing temperature is 250～450 DEG C, preferably 300～400 DEG C, insulation 2～20h.
Further, the processing technology of above-mentioned raising 2 × × × line aluminium alloy sheet material antifatigue damage performance, wherein: for thinPanel products, cold rolling and intermediate annealing operation selectively repeatedly.
Further, the processing technology of above-mentioned raising 2 × × × line aluminium alloy sheet material antifatigue damage performance, wherein: described stepSuddenly the alloy material composition in (1) is 2 × × × line aluminium alloy including AA2024, AA2524.
Further, the processing technology of above-mentioned raising 2 × × × line aluminium alloy sheet material antifatigue damage performance, wherein: described stepSuddenly in (4), reply preferably 270～300 DEG C of Pre-annealing Temperatures, temperature retention time is 4～8h preferably.
Substantive distinguishing features of the present invention and significant technological progress are embodied in: reply preannealing technique by increase, can make sheet materialThe L-ST cross section average equivalent diameter of crystal grain is controlled between 30～150 μ m, and crystal grain length-width ratio is controlled between 2.5～7.0; WhenR=0.1, loading frequency f=2～10HZ, when 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 all meet the requirement of AMS4296 air standard; In addition, thisBright being widely used, is not only suitable for the 2 × × × line aluminium alloy sheet material for aircraft skin including AA2024, AA2524, otherThe aluminum alloy plate materials that need to improve antifatigue damage performance also can adopt the method to prepare.
Brief description of the drawings
Fig. 1 is the technological process of preparation 2 × × ×-T3 aluminium alloy thick plate;
Fig. 2 is the technological process of preparation 2 × × ×-T3 Aluminum Alloy Plate;
Fig. 3 is the technological process of preparation 2 × × ×-T3 aluminium alloy sheet.
Fig. 4 is the metallographic microstructure of the D/4 position, 2524-T3 slab L-ST cross section of embodiment 1.
Fig. 5 is the metallographic microstructure in the 2524-T3 cut deal L-ST cross section of embodiment 2 and comparative example 1.
Fig. 6 is the metallographic microstructure in the 2524-T3 thin plate L-ST cross section of embodiment 4 and comparative example 3.
Detailed description of the invention
Below in conjunction with accompanying drawing table, specific embodiment and comparative example, the specific embodiment of the present invention is described in further detail, so thatTechnical solution of the present invention is easier to understand and grasp.
One proposed by the invention improves the processing technology of 2 × × × line aluminium alloy sheet material antifatigue damage performance, it is characterized in thatComprise the following steps:
(1), according to the melting of preparing burden of 2 × × × line aluminium alloy composition and content range thereof, casting obtains required ingot casting, alloy materialMaterial composition is 2 × × × line aluminium alloy including AA2024, AA2524;
(2) ingot casting is carried out to homogenising processing, milling face and alclad successively, carry out again afterwards preheating and hot roughing, make heat thickRoll plate;
(3) by hot roughing plate hot finishing, cold roller and deformed to finished product sheet metal thickness; For slab product, its finished product sheet metal thickness>=4.0mm, is preferably >=5.0mm, by hot finishing to finished product sheet metal thickness; For cut deal product, its finished product sheet metal thicknessBe 2.0～6.0mm, be preferably 2.5～5.0mm, by being deformed into finished product sheet metal thickness through cold finish to gauge after hot finishing; For thinPanel products, its finished product sheet metal thickness < 2.5mm, is preferably≤2.0mm, by after hot finishing through cold rolling, intermediate annealing and cold endRoll and be deformed into finished product sheet metal thickness.
(4) sheet material that is rolled to finished product sheet metal thickness is replied to preannealing processing, reply the temperature of preannealing and be 250～320 DEG C, temperature retention time is 2～20h;
(5) will carry out solution hardening processing through the sheet material of replying preannealing processing, solid solubility temperature is 480～505 DEG C, when insulationBetween be 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%. Produce for thin plateProduct, cold rolling intermediate annealing temperature is 250～450 DEG C, preferably 300～400 DEG C, insulation 2～20h. And, produce for thin plateProduct, cold rolling and intermediate annealing operation selectively repeatedly. Reply in described step (4) Pre-annealing Temperature preferably 270～300 DEG C, temperature retention time is 4～8h preferably.
Embodiment 1
Press the unit of 4.32wt.%Cu, 1.35wt.%Mg, 0.61wt.%Mn, 0.08wt.%Fe, 0.06wt.%Si, 0.03wt.%TiElement proportioning founding 400 × 1620 × 2500mm specification 2524 aluminium alloy cast ingots. Alloy cast ingot is carried out to 498 DEG C/32h successively evenChange processing, milling face, alclad, 480 DEG C/8h preheating, in 480 DEG C of hot roughing, and then hot finishing is to 6.0mm afterwards. By heatFinish rolling plate is in 290 DEG C of insulation 4h, afterwards through 496 DEG C/50min solution hardening, straightening processing with more than natrual ageing 96h, and workProcess flow as shown in Figure 1. The tensile mechanical properties of test final finished sheet material, and press GB/T6398-2000 and AMS4296The fatigue crack growth rate of standard testing sheet material.
Embodiment 2
Press the unit of 4.32wt.%Cu, 1.35wt.%Mg, 0.61wt.%Mn, 0.08wt.%Fe, 0.06wt.%Si, 0.03wt.%TiElement proportioning founding 400 × 1620 × 2500mm specification 2524 aluminium alloy cast ingots. Ingot casting is carried out to 498 DEG C/32h homogenising place successivelyReason, milling face, alclad, 480 DEG C/8h preheating, 480 DEG C of hot roughing, and then hot finishing is to 6.0mm afterwards. By hot finishingPlate is deformed into 2.5mm by the cold finish to gauge of 58% reduction ratio, and cold finish to gauge plate is in 270 DEG C of insulation 8h, solid through 496 DEG C/25min afterwardsMolten quenching, after straightening processing more than natrual ageing 96h, technological process as shown in Figure 2 again. The power of test final finished sheet materialLearn performance, and press the fatigue crack growth rate of GB/T6398-2000 and AMS4296 standard testing sheet material.
Embodiment 3
Press the unit of 4.32wt.%Cu, 1.35wt.%Mg, 0.61wt.%Mn, 0.08wt.%Fe, 0.06wt.%Si, 0.03wt.%TiElement proportioning founding 400 × 1620 × 2500mm specification 2524 aluminium alloy cast ingots. Ingot casting is carried out to 498 DEG C/32h homogenising place successivelyReason, milling face, alclad, 480 DEG C/8h preheating, 480 DEG C of hot roughing, and then hot finishing is to 6.0mm afterwards. By hot finishingPlate is deformed into 2.5mm by the cold finish to gauge of 58% reduction ratio, and cold finish to gauge plate is in 290 DEG C of insulation 4h, solid through 496 DEG C/25min afterwardsMolten quenching, after straightening processing more than natrual ageing 96h, technological process as shown in Figure 2 again. The power of test final finished sheet materialLearn performance, and press the fatigue crack growth rate of GB/T6398-2000 and AMS4296 standard testing sheet material.
Embodiment 4
Press the unit of 4.28wt.%Cu, 1.30wt.%Mg, 0.60wt.%Mn, 0.08wt.%Fe, 0.06wt.%Si, 0.03wt.%TiElement proportioning founding 400 × 1620 × 2500mm specification 2524 aluminium alloy cast ingots. Ingot casting is carried out to 498 DEG C/30h homogenising place successivelyReason, milling face, alclad, 485 DEG C/8h preheating, hot roughing and hot finishing are to 4.5mm. Hot finishing plate is cold by 56% reduction ratioRoll and be deformed into 2.0mm, then be deformed into 0.8mm through 340 DEG C/4h intermediate annealing with by the cold finish to gauge of 60% reduction ratio. By cold finish to gaugePlate is in 275 DEG C of insulation 8h, afterwards through 498 DEG C/16min solution hardening, and again after straightening processing more than natrual ageing 96h, workProcess flow as shown in Figure 3. The mechanical property of test final finished sheet material, and press GB/T6398-2000 and AMS4296 markThe fatigue crack growth rate of accurate test sheet material.
Embodiment 5
Press the unit of 4.28wt.%Cu, 1.30wt.%Mg, 0.60wt.%Mn, 0.08wt.%Fe, 0.06wt.%Si, 0.03wt.%TiElement proportioning founding 400 × 1620 × 2500mm specification 2524 aluminium alloy cast ingots. Ingot casting is carried out to 498 DEG C/30h homogenising place successivelyReason, milling face, alclad, 485 DEG C/8h preheating, hot roughing and hot finishing are to 4.5mm. Hot finishing plate is cold by 56% reduction ratioRoll and be deformed into 2.0mm, then be deformed into 0.8mm through 340 DEG C/4h intermediate annealing with by the cold finish to gauge of 60% reduction ratio. By cold finish to gaugePlate is in 290 DEG C of insulation 4h, afterwards through 498 DEG C/16min solution hardening, and again after straightening processing more than natrual ageing 96h, workProcess flow as shown in Figure 3. The mechanical property of test final finished sheet material, and press GB/T6398-2000 and AMS4296 markThe fatigue crack growth rate of accurate test sheet material.
Comparative example 1
Press the unit of 4.32wt.%Cu, 1.35wt.%Mg, 0.61wt.%Mn, 0.08wt.%Fe, 0.06wt.%Si, 0.03wt.%TiElement proportioning founding 400 × 1620 × 2500mm specification 2524 aluminium alloy cast ingots. Ingot casting is carried out to 498 DEG C/32h homogenising place successivelyReason, milling face, alclad, 480 DEG C/8h preheating, in 480 DEG C of hot roughing, and then hot finishing is to 6.0mm afterwards. By hot finishingPlate is deformed into 2.5mm by the cold finish to gauge of 58% reduction ratio, then directly through 496 DEG C/25min solution hardening, then after straightening processingMore than natrual ageing 96h. The mechanical property of test final finished sheet material, and press GB/T6398-2000 and AMS4296 markThe fatigue crack growth rate of accurate test sheet material.
Comparative example 2
Press the unit of 4.32wt.%Cu, 1.35wt.%Mg, 0.61wt.%Mn, 0.08wt.%Fe, 0.06wt.%Si, 0.03wt.%TiElement proportioning founding 400 × 1620 × 2500mm specification 2524 aluminium alloy cast ingots. Ingot casting is carried out to 498 DEG C/32h homogenising place successivelyReason, milling face, alclad, 480 DEG C/8h preheating, 480 DEG C of hot roughing, and then hot finishing is to 6.0mm afterwards. By hot finishingPlate is deformed into 2.5mm by the cold finish to gauge of 58% reduction ratio, by cold-reduced sheet in 200 DEG C insulation 4h, afterwards through 496 DEG C/25min solid solutionQuench, after straightening processing more than natrual ageing 96h, technological process as shown in Figure 2 again. The mechanics of test final finished sheet materialPerformance, and press the fatigue crack growth rate of GB/T6398-2000 and AMS4296 standard testing sheet material.
Comparative example 3
Press the unit of 4.28wt.%Cu, 1.30wt.%Mg, 0.60wt.%Mn, 0.08wt.%Fe, 0.06wt.%Si, 0.03wt.%TiElement proportioning founding 400 × 1620 × 2500mm specification 2524 aluminium alloy cast ingots. Ingot casting is carried out to 498 DEG C/30h homogenising place successivelyReason, milling face, alclad, 485 DEG C/8h preheating, 485 DEG C of hot roughing, and then hot finishing is to 4.5mm afterwards. By hot finishingPlate is cold roller and deformed to 2.0mm by 56% reduction ratio, then is deformed into through 340 DEG C/4h intermediate annealing with by the cold finish to gauge of 60% reduction ratio0.8mm. By cold-reduced sheet directly through 498 DEG C/16min solution hardening, again after straightening processing more than natrual ageing 96h. TestThe mechanical property of final finished sheet material, and the fatigue crack expansion of pressing GB/T6398-2000 and AMS4296 standard testing sheet materialExhibition speed.
Comparative example 4
Press the unit of 4.28wt.%Cu, 1.30wt.%Mg, 0.60wt.%Mn, 0.08wt.%Fe, 0.06wt.%Si, 0.03wt.%TiElement proportioning founding 400 × 1620 × 2500mm specification 2524 aluminium alloy cast ingots. Ingot casting is carried out to 498 DEG C/30h homogenising place successivelyReason, milling face, alclad, 485 DEG C/8h preheating, hot roughing and hot finishing are to 4.5mm. Hot finishing plate is cold by 56% reduction ratioRoll and be deformed into 2.0mm, then be deformed into 0.8mm through 340 DEG C/4h intermediate annealing with by the cold finish to gauge of 60% reduction ratio. By cold finish to gaugePlate is in 225 DEG C of insulation 4h, afterwards through 498 DEG C/16min solution hardening, and again after straightening processing more than natrual ageing 96h, workProcess flow as shown in Figure 3. The mechanical property of test final finished sheet material, and press GB/T6398-2000 and AMS4296 markThe fatigue crack growth rate of accurate test sheet material.
Table 1 is for producing the technological parameter of 2524-T3 aluminum alloy plate materials in embodiment and comparative example, table 2 has provided embodiment and ratioThe fatigue crack prop-agation speed of 2524-T3 aluminium alloy finished product sheet material in more routine.
As can be seen from Table 1, all experience reply preannealing before rolling in an embodiment plate solution hardening, and replied preannealingTime long enough; And in comparative example, comparative example 1 and comparative example 3 solution hardening are front without replying preannealing processing, comparative example 2Although with before comparative example 4 solution hardening through replying preannealing processing, temperature retention time is shorter.
As can be seen from Table 2, the average equivalent diameter of crystal grain of the 2524-T3 sheet material of embodiment 1,2,3,4 and 5 is all largeIn 30 μ m, length-width ratio is also greater than 2.5. Fig. 4 is the production board metallographic overlay film photo of embodiment 1, and in figure, sheet material crystal grain on average etc.Effect diameter is 70 μ m, and length-width ratio is 6.5. The fatigue crack growth rate da/dN < of acetonideexample 2524-T3 sheet material3.05×10-3Mm/cycle, fatigue crack growth rate and mechanical property all meet the requirement of AMS4296 air standard. And compareThe 2524-T3 sheet material grain size of example 1,2,3 and 4 is less than 30 μ m or length-width ratio is less than 2.5, although mechanical propertyMeet the requirement of AMS4296 air standard, but fatigue crack growth rate da/dN > 3.05 × 10-3Mm/cycle, does not meetThe requirement of AMS4296 air standard. Comparative example 2 and comparative example 1 and embodiment 4 and comparative example 3, because solid solution is advancedGone the processing of reply preannealing, the crystallite dimension of embodiment 2 and embodiment 4 and length-width ratio are than comparative example 1 and comparative example 3 allGreatly, Fig. 5 (a), Fig. 5 (b) be corresponding embodiment 2 and comparative example 1 respectively, and Fig. 6 (a), Fig. 6 (b) be corresponding embodiment 4 and ratio respectivelyExample 3. Comparative example 2,3 and comparative example 2 and embodiment 4,5 and comparative example 4, the crystallite dimension of embodiment and length and widthThan being all greater than comparative example, explanation should make to reply preannealing holding time long before solid solution, could effectively increase finished product lath grain chiVery little and length-width ratio. As can be seen here, adopt control of the present invention to reply preannealing technique, can effectively regulate and control 2524-T3 sheet materialCrystallite dimension and pattern, thereby reduce significantly 2 × × ×-T3 sheet material fatigue crack growth rate da/dN value.
Certainly, above is only concrete exemplary applications of the present invention, and protection scope of the present invention is not constituted any limitation. All employingsEquivalents or equivalence are replaced and the technical scheme of formation, within all dropping on rights protection scope of the present invention.
Table 1 is the technological parameter of preparation 2524-T3 aluminum alloy plate materials
The Microstructure and properties test result that table 2 is the 2524-T3 sheet material prepared by table 1 technique
Note: grain size is crystal grain homalographic diameter of a circle, crystal grain average area=crystal grain major axis (L) long mean value × crystal grain minor axis (S) is longMean value. The long mean value of the long mean value/crystal grain of length-width ratio=crystal grain major axis minor axis.
Claims (7)
1. the processing technology that improves 2 × × × line aluminium alloy sheet material antifatigue damage performance, is characterized in that comprising the following steps:
(1), according to the melting of preparing burden of 2 × × × line aluminium alloy composition and content range thereof, casting obtains required ingot casting;
(2) ingot casting is carried out to homogenising processing, milling face and alclad successively, carry out again afterwards preheating and hot roughing, make hot roughing plate;
(3) by hot roughing plate hot finishing, cold roller and deformed to finished product sheet metal thickness;
(4) sheet material that is rolled to finished product sheet metal thickness is replied to preannealing processing, the temperature of replying preannealing is 250～320 DEG C, and temperature retention time is 2～20h;
(5) will carry out solution hardening processing through the sheet material of replying preannealing processing, solid solubility temperature is 480～505 DEG C, and temperature retention time is 3～60min;
(6) sheet material after solution hardening is aligned, and natrual ageing is to stable state.
2. the processing technology of raising 2 according to claim 1 × × × line aluminium alloy sheet material antifatigue damage performance, is characterized in that: in described step (3) for slab product, its finished product sheet metal thickness>=4.0mm, by hot finishing to finished product sheet metal thickness; For cut deal product, its finished product sheet metal thickness is 2.0～6.0mm, by being deformed into finished product sheet metal thickness through cold finish to gauge after hot finishing; For light sheet products, its finished product sheet metal thickness<2.5mm, by being deformed into finished product sheet metal thickness through cold rolling, intermediate annealing and cold finish to gauge after hot finishing.
3. the processing technology of raising 2 according to claim 2 × × × line aluminium alloy sheet material antifatigue damage performance, is characterized in that: in described step (3), for cut deal and light sheet products, cold finish to gauge reduction ratio is 40～75%.
4. the processing technology of raising 2 according to claim 2 × × × line aluminium alloy sheet material antifatigue damage performance, is characterized in that: for light sheet products, cold rolling intermediate annealing temperature is 250～450 DEG C, insulation 2～20h.
5. the processing technology of raising 2 according to claim 2 × × × line aluminium alloy sheet material antifatigue damage performance, is characterized in that: for light sheet products, cold rolling and intermediate annealing operation selectively repeatedly.
6. the processing technology of raising 2 according to claim 1 × × × line aluminium alloy sheet material antifatigue damage performance, is characterized in that: the alloy material composition in described step (1) is 2 × × × line aluminium alloy including AA2024, AA2524.
7. the processing technology of raising 2 according to claim 1 × × × line aluminium alloy sheet material antifatigue damage performance, is characterized in that: in described step (4), replying Pre-annealing Temperature is 270～300 DEG C, and temperature retention time is 4～8h.
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| 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 |
| CN113201641A (en) * | 2021-04-26 | 2021-08-03 | 瑞安市创博机械有限公司 | Heat treatment method and heat treatment method of stretched aluminum guide roller |
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| CN103045976A (en) * | 2012-12-27 | 2013-04-17 | 中南大学 | Heat treatment method capable of improving anti-fatigue performance of aluminum alloy |
| CN103589977A (en) * | 2013-11-11 | 2014-02-19 | 中南大学 | Method for improving the fatigue resistance performance of Al-Cu-Mg alloy |
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| CN101967615A (en) * | 2010-10-27 | 2011-02-09 | 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 |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| 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 |
| CN113201641A (en) * | 2021-04-26 | 2021-08-03 | 瑞安市创博机械有限公司 | Heat treatment method and heat treatment method of stretched aluminum guide roller |
| 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 |
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