CN103952652B - A kind of manufacture method of aviation aluminum alloy pre-stretching plate - Google Patents
A kind of manufacture method of aviation aluminum alloy pre-stretching plate Download PDFInfo
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Abstract
A manufacture method for aviation aluminum alloy pre-stretching plate, the present invention relates to the manufacture method of aluminum alloy plate materials.The present invention will solve existing aluminum alloy plate materials, and to there is intensity, elongation after fracture, fracture toughness, corrosive nature and specific conductivity low, and sheet material 100% flaw detection cannot meet the problem of A grade standard requirement.Method: one, prepare molten aluminium alloy; Two, the side's of preparation ingot casting; Three, anneal; Four, aluminum alloy square ingot casting is prepared; Five, sheet material blank is prepared; Six, heat; Seven, aluminum alloy plate materials is prepared; Eight, cut off; Nine, solution treatment and quenching; Ten, tension leveling; 11, ageing treatment; 12, cut saw, namely obtain aviation aluminum alloy pre-stretching plate.The present invention is used for a kind of manufacture method of aviation aluminum alloy pre-stretching plate.
Description
Technical field
The present invention relates to the manufacture method of aluminum alloy plate materials.
Background technology
At present, China's aeronautical product needs a kind of special sheet material, requires that this kind of aluminum alloy T 7451 state sheet material endwise tensile strength is not less than 510N/mm
2, Proof strength of non-proportional is not less than 441N/mm
2, elongation after fracture is not less than 10%, and fracture toughness is not less than 32N/mm
2.m
1/2; The transverse tensile strength of sheet material is not less than 510N/mm
2, Proof strength of non-proportional is not less than 441N/mm
2, elongation after fracture is not less than 9%, and fracture toughness is not less than 27N/mm
2.m
1/2; The exfoliation Corrosion of sheet material is not less than EB level; C Zernike annular polynomial corrosive nature is for adding 241N/mm
2power tests 30 days without any cracking phenomena; Conductivity value is not less than 22MS/m; Sheet material 100% flaw detection meets the requirement of A grade standard, but all kinds of aluminum alloy plate materials of existing explained hereafter cannot meet the application requiring of this kind of aviation articles for use.
Summary of the invention
The present invention will solve existing aluminum alloy plate materials, and to there is intensity, elongation after fracture, fracture toughness, corrosive nature and specific conductivity low, and sheet material 100% flaw detection cannot meet the problem of A grade standard requirement, and provide a kind of manufacture method of aviation aluminum alloy pre-stretching plate.
A manufacture method for aviation aluminum alloy pre-stretching plate, specifically carry out according to following steps:
One, molten aluminium alloy is prepared: be first that aluminium takes aluminium ingot, copper ingot, magnesium ingot, zinc ingot metal, aluminium zirconium alloy ingot, aluminum titanium alloy ingot and aluminium Ti, B grain graining agent by massfraction 5.7% ~ 6.7%Zn, 1.9% ~ 2.6%Mg, 2.0% ~ 2.6%Cu, 0.08% ~ 0.15%Zr, 0.001% ~ 0.12%Si, 0.001% ~ 0.15%Fe, 0.001% ~ 0.1%Mn, 0.001% ~ 0.04%Cr, 0.001% ~ 0.06%Ti and surplus, then be melting 6h ~ 9h in the smelting furnace of 720 DEG C ~ 760 DEG C in temperature, obtain molten aluminium alloy;
Two, the side's of preparation ingot casting: being cast as thick at the molten aluminium alloy that casting temp is 705 DEG C ~ 730 DEG C, casting speed is 35mm/min ~ 45mm/min, step one obtains under be 10 DEG C ~ 20 DEG C and water coolant intensity being the condition of 0.01MPa ~ 0.05MPa by temperature of cooling water is 440mm and the wide square ingot casting for 1300mm;
Three, anneal: square ingot casting step 2 obtained is incubated 47h ~ 50h under temperature is the condition of 460 DEG C ~ 475 DEG C, naturally cool to room temperature after coming out of the stove and obtain the square ingot casting after annealing;
Four, prepare aluminum alloy square ingot casting: use planer that the square ingot casting after annealing is gone the casting oxide skin on surface under room temperature condition, obtaining thick is 380mm ~ 390mm and the wide aluminum alloy square ingot casting for 1250mm;
Five, prepare sheet material blank: use under room temperature condition sawing machine by thick be 1320mm for 380mm ~ 390mm and the wide aluminum alloy square ingot casting for 1250mm cut into length, thick be 380mm ~ 390mm and the wide sheet material blank for 1250mm;
Six, heat: temperature put into by sheet material blank step 5 obtained is that the resistance heading furnace of 375 DEG C ~ 420 DEG C heats, and heat-up time is 12h ~ 16h, obtains hot sheet blank;
Seven, aluminum alloy plate materials is prepared: hot sheet blank step 6 obtained uses mill milling under start rolling temperature is 380 DEG C ~ 420 DEG C and finishing temperature is the condition of 350 DEG C ~ 370 DEG C, obtains aluminum alloy plate materials;
Eight, cut off: use sawing machine to excise the defect part of aluminum alloy plate materials under room temperature condition, obtain the aluminum alloy plate materials that quality is homogeneous;
Nine, solution treatment and quenching: be use stove at the bottom of roller to carry out solution treatment under the condition of 465 DEG C ~ 475 DEG C in temperature by aluminum alloy plate materials homogeneous for quality, treatment time is 1h ~ 3h, then be the quenching-in water 0s ~ 30s of 0 DEG C ~ 35 DEG C in temperature, obtain the aluminum alloy plate materials after quenching;
Ten, tension leveling: be carry out tension leveling by drawing die under the condition of 1.5% ~ 3% at stretching pass deformation rate by the aluminum alloy plate materials after quenching, obtain the aluminum alloy plate materials after stretching;
11, ageing treatment: by the aluminum alloy plate materials after stretching at temperature is 105 DEG C ~ 125 DEG C, insulation 4h ~ 8h, then temperature is raised to 165 DEG C ~ 175 DEG C from 105 DEG C ~ 125 DEG C, and be incubated 20h ~ 26h under the condition of 165 DEG C ~ 175 DEG C in temperature, obtain the aluminum alloy plate materials after ageing treatment;
12, saw is cut: the aluminum alloy plate materials after using sawing machine to cut saw ageing treatment under room temperature condition, obtains aviation aluminum alloy pre-stretching plate.
The invention has the beneficial effects as follows: the present invention is by the founding tackling key problem of optimized alloy composition, this alloy large gauge side ingot casting, the rolling optimizing sheet material, solution treatment, aging treatment process, produce this sheet alloy, reach the over-all properties demand of user to this sheet alloy, aluminum alloy plate materials entity size, the surface quality of preparation are good, in industrial production, processability is good, and comprehensive mechanical property is excellent.Test aviation aluminum alloy pre-stretching plate endwise tensile strength prepared by the present invention by GB/T228 " metallic substance room temperature tensile properties test method " and be not less than 510N/mm
2, Proof strength of non-proportional is not less than 441N/mm
2, elongation after fracture is not less than 10%; The transverse tensile strength of sheet material is not less than 510N/mm
2, Proof strength of non-proportional is not less than 441N/mm
2, elongation after fracture is not less than 9%; By GB/T4161 " metallic substance Plane Strain Fracture Toughness K
iCtest method " the longitudinal fracture toughness of testing aviation aluminum alloy pre-stretching plate prepared by the present invention is not less than 32N/mm
2.m
1/2, strength transverse rupture strength is not less than 27N/mm
2.m
1/2; The exfoliation Corrosion being tested aviation aluminum alloy pre-stretching plate prepared by the present invention by HB5455 " aluminium alloy breakaway corrosion test method " is not less than EB level; The C Zernike annular polynomial corrosive nature of aviation aluminum alloy pre-stretching plate prepared by the present invention is tested for adding 241N/mm by HB5259 " aluminum alloy C ring sample stress corrosion (cracking) test method "
2power 30 days is without any cracking phenomena; The conductivity value being tested aviation aluminum alloy pre-stretching plate prepared by the present invention by GB/T12966 " aluminium alloy Eddy Conductivity testing method " is not less than 22.0MS/m, test aviation aluminum alloy pre-stretching plate 100% flaw detection prepared by the present invention by ASTMB594 " ultrasonic testing of aviation alloyed aluminium converted products " and meet the requirement of A grade standard, be applicable to making aviation product.
Embodiment
Technical solution of the present invention is not limited to following cited embodiment, also comprises the arbitrary combination between each embodiment.
Embodiment one: the manufacture method of a kind of aviation aluminum alloy pre-stretching plate described in present embodiment, specifically carry out according to following steps:
One, molten aluminium alloy is prepared: be first that aluminium takes aluminium ingot, copper ingot, magnesium ingot, zinc ingot metal, aluminium zirconium alloy ingot, aluminum titanium alloy ingot and aluminium Ti, B grain graining agent by massfraction 5.7% ~ 6.7%Zn, 1.9% ~ 2.6%Mg, 2.0% ~ 2.6%Cu, 0.08% ~ 0.15%Zr, 0.001% ~ 0.12%Si, 0.001% ~ 0.15%Fe, 0.001% ~ 0.1%Mn, 0.001% ~ 0.04%Cr, 0.001% ~ 0.06%Ti and surplus, then be melting 6h ~ 9h in the smelting furnace of 720 DEG C ~ 760 DEG C in temperature, obtain molten aluminium alloy;
Two, the side's of preparation ingot casting: being cast as thick at the molten aluminium alloy that casting temp is 705 DEG C ~ 730 DEG C, casting speed is 35mm/min ~ 45mm/min, step one obtains under be 10 DEG C ~ 20 DEG C and water coolant intensity being the condition of 0.01MPa ~ 0.05MPa by temperature of cooling water is 440mm and the wide square ingot casting for 1300mm;
Three, anneal: square ingot casting step 2 obtained is incubated 47h ~ 50h under temperature is the condition of 460 DEG C ~ 475 DEG C, naturally cool to room temperature after coming out of the stove and obtain the square ingot casting after annealing;
Four, prepare aluminum alloy square ingot casting: use planer that the square ingot casting after annealing is gone the casting oxide skin on surface under room temperature condition, obtaining thick is 380mm ~ 390mm and the wide aluminum alloy square ingot casting for 1250mm;
Five, prepare sheet material blank: use under room temperature condition sawing machine by thick be 1320mm for 380mm ~ 390mm and the wide aluminum alloy square ingot casting for 1250mm cut into length, thick be 380mm ~ 390mm and the wide sheet material blank for 1250mm;
Six, heat: temperature put into by sheet material blank step 5 obtained is that the resistance heading furnace of 375 DEG C ~ 420 DEG C heats, and heat-up time is 12h ~ 16h, obtains hot sheet blank;
Seven, aluminum alloy plate materials is prepared: hot sheet blank step 6 obtained uses mill milling under start rolling temperature is 380 DEG C ~ 420 DEG C and finishing temperature is the condition of 350 DEG C ~ 370 DEG C, obtains aluminum alloy plate materials;
Eight, cut off: use sawing machine to excise the defect part of aluminum alloy plate materials under room temperature condition, obtain the aluminum alloy plate materials that quality is homogeneous;
Nine, solution treatment and quenching: be use stove at the bottom of roller to carry out solution treatment under the condition of 465 DEG C ~ 475 DEG C in temperature by aluminum alloy plate materials homogeneous for quality, treatment time is 1h ~ 3h, then be the quenching-in water 0s ~ 30s of 0 DEG C ~ 35 DEG C in temperature, obtain the aluminum alloy plate materials after quenching;
Ten, tension leveling: be carry out tension leveling by drawing die under the condition of 1.5% ~ 3% at stretching pass deformation rate by the aluminum alloy plate materials after quenching, obtain the aluminum alloy plate materials after stretching;
11, ageing treatment: by the aluminum alloy plate materials after stretching at temperature is 105 DEG C ~ 125 DEG C, insulation 4h ~ 8h, then temperature is raised to 165 DEG C ~ 175 DEG C from 105 DEG C ~ 125 DEG C, and be incubated 20h ~ 26h under the condition of 165 DEG C ~ 175 DEG C in temperature, obtain the aluminum alloy plate materials after ageing treatment;
12, saw is cut: the aluminum alloy plate materials after using sawing machine to cut saw ageing treatment under room temperature condition, obtains aviation aluminum alloy pre-stretching plate.
The impurity elements such as Si and Fe in present embodiment derive from aluminium ingot.
Impurity Si≤0.12%, Fe≤0.15% in the aluminum alloy plate materials of present embodiment, other single impurity≤0.05%, the performance of the impurity within the scope of this on aluminum alloy plate materials does not affect.
Present embodiment step 11 by stretch after aluminum alloy plate materials at temperature is 105 DEG C ~ 125 DEG C, insulation 4h ~ 8h, then sheet material heats up with stove in stove, temperature is raised to 165 DEG C ~ 175 DEG C from 105 DEG C ~ 125 DEG C, and be incubated 20h ~ 26h under the condition of 165 DEG C ~ 175 DEG C in temperature, obtain aviation aluminum alloy pre-stretching plate.
The beneficial effect of present embodiment is: present embodiment is by the founding tackling key problem of optimized alloy composition, this alloy large gauge side ingot casting, the rolling optimizing sheet material, solution treatment, aging treatment process, produce this sheet alloy, reach the over-all properties demand of user to this sheet alloy, aluminum alloy plate materials entity size, the surface quality of preparation are good, in industrial production, processability is good, and comprehensive mechanical property is excellent.Test aviation aluminum alloy pre-stretching plate endwise tensile strength prepared by present embodiment by GB/T228 " metallic substance room temperature tensile properties test method " and be not less than 510N/mm
2, Proof strength of non-proportional is not less than 441N/mm
2, elongation after fracture is not less than 10%; The transverse tensile strength of sheet material is not less than 510N/mm
2, Proof strength of non-proportional is not less than 441N/mm
2, elongation after fracture is not less than 9%; By GB/T4161 " metallic substance Plane Strain Fracture Toughness K
iCtest method " the longitudinal fracture toughness of testing aviation aluminum alloy pre-stretching plate prepared by present embodiment is not less than 32N/mm
2.m
1/2, strength transverse rupture strength is not less than 27N/mm
2.m
1/2; The exfoliation Corrosion being tested aviation aluminum alloy pre-stretching plate prepared by present embodiment by HB5455 " aluminium alloy breakaway corrosion test method " is not less than EB level; The C Zernike annular polynomial corrosive nature of aviation aluminum alloy pre-stretching plate prepared by present embodiment is tested for adding 241N/mm by HB5259 " aluminum alloy C ring sample stress corrosion (cracking) test method "
2power 30 days is without any cracking phenomena; The conductivity value being tested aviation aluminum alloy pre-stretching plate prepared by present embodiment by GB/T12966 " aluminium alloy Eddy Conductivity testing method " is not less than 22.0MS/m, test aviation aluminum alloy pre-stretching plate 100% flaw detection prepared by present embodiment by ASTMB594 " ultrasonic testing of aviation alloyed aluminium converted products " and meet the requirement of A grade standard, be applicable to making aviation product.
Embodiment two: present embodiment and embodiment one unlike: be first that aluminium takes aluminium ingot, copper ingot, magnesium ingot, zinc ingot metal, aluminium zirconium alloy ingot, aluminum titanium alloy ingot and aluminium Ti, B grain graining agent by massfraction 6.3%Zn, 2.3%Mg, 2.1%Cu, 0.11%Zr, 0.5%Si, 0.8%Fe, 0.05%Mn, 0.02%Cr, 0.03%Ti and surplus in step one, then be melting 8h in the smelting furnace of 725 DEG C in temperature, obtain molten aluminium alloy.Other is identical with embodiment one.
Embodiment three: one of present embodiment and embodiment one or two unlike: being cast as thick at the molten aluminium alloy that casting temp is 710 DEG C, casting speed is 40mm/min, step one obtains under be 16 DEG C and water coolant intensity being the condition of 0.02MPa by temperature of cooling water in step 2 is 440mm and the wide square ingot casting for 1300mm.Other is identical with embodiment one or two.
Embodiment four: one of present embodiment and embodiment one to three are be incubated 48h under the condition of 470 DEG C in temperature unlike: square ingot casting step 2 obtained in step 3, naturally cool to room temperature and obtain the square ingot casting after annealing after coming out of the stove.Other is identical with embodiment one to three.
Embodiment five: one of present embodiment and embodiment one to four unlike: use under room temperature condition in step 5 sawing machine by thick be 1320mm for 380mm ~ 390mm and the wide aluminum alloy square ingot casting for 1250mm cut into length, thick be 385mm and the wide sheet material blank for 1250mm.Other is identical with embodiment one to four.
Embodiment six: it is that the resistance heading furnace of 410 DEG C heats that one of present embodiment and embodiment one to five put into temperature unlike: sheet material blank step 5 obtained in step 6, and heat-up time is 12h, obtains hot sheet blank.Other is identical with embodiment one to five.
Embodiment seven: one of present embodiment and embodiment one to six use mill milling unlike: hot sheet blank step 6 obtained in step 7 under start rolling temperature is 400 DEG C and finishing temperature is the condition of 365 DEG C, obtain aluminum alloy plate materials.Other is identical with embodiment one to six.
Embodiment eight: one of present embodiment and embodiment one to seven unlike: be use stove at the bottom of roller to carry out solution treatment under the condition of 475 DEG C in temperature by aluminum alloy plate materials homogeneous for quality in step 9, treatment time is 2h, then be the quenching-in water 20s of 18 DEG C in temperature, obtain the aluminum alloy plate materials after quenching.Other is identical with embodiment one to seven.
Embodiment nine: one of present embodiment and embodiment one to eight unlike: the aluminum alloy plate materials after quenching step 9 obtained in step 10 carries out tension leveling by drawing die under stretching pass deformation rate is the condition of 2.2%, obtain stretch after aluminum alloy plate materials.Other is identical with embodiment one to eight.
Embodiment ten: one of present embodiment and embodiment one to nine unlike: in step 11 by stretch after aluminum alloy plate materials at temperature is 120 DEG C, insulation 6h, then temperature is raised to 170 DEG C from 120 DEG C, and be incubated 24h under the condition of 170 DEG C in temperature, obtain the aluminum alloy plate materials after ageing treatment.Other is identical with embodiment one to nine.
Following examples are adopted to verify beneficial effect of the present invention:
Embodiment:
The manufacture method of a kind of aviation aluminum alloy pre-stretching plate described in the present embodiment, specifically carry out according to following steps:
One, molten aluminium alloy is prepared: be first that aluminium takes aluminium ingot, copper ingot, magnesium ingot, zinc ingot metal, aluminium zirconium alloy ingot, aluminum titanium alloy ingot and aluminium Ti, B grain graining agent by massfraction 6.3%Zn, 2.3%Mg, 2.1%Cu, 0.11%Zr, 0.5%Si, 0.8%Fe, 0.05%Mn, 0.02%Cr, 0.03%Ti and surplus, then be melting 8h in the smelting furnace of 725 DEG C in temperature, obtain molten aluminium alloy;
Two, the side's of preparation ingot casting: being cast as thick at the molten aluminium alloy that casting temp is 710 DEG C, casting speed is 40mm/min, step one obtains under be 16 DEG C and water coolant intensity being the condition of 0.02MPa by temperature of cooling water is 440mm and the wide square ingot casting for 1300mm;
Three, anneal: square ingot casting step 2 obtained is be incubated 48h under the condition of 470 DEG C in temperature, naturally cool to room temperature after coming out of the stove and obtain the square ingot casting after annealing;
Four, prepare aluminum alloy square ingot casting: use planer that the square ingot casting after annealing is gone the casting oxide skin on surface under room temperature condition, obtaining thick is 385mm and the wide aluminum alloy square ingot casting for 1250mm;
Five, prepare sheet material blank: use under room temperature condition sawing machine by thick be 1320mm for 385mm and the wide aluminum alloy square ingot casting for 1250mm cut into length, thick be 385mm and the wide sheet material blank for 1250mm;
Six, heat: temperature put into by sheet material blank step 5 obtained is that the resistance heading furnace of 410 DEG C heats, and heat-up time is 12h, obtains hot sheet blank;
Seven, aluminum alloy plate materials is prepared: hot sheet blank step 6 obtained uses mill milling under start rolling temperature is 400 DEG C and finishing temperature is the condition of 365 DEG C, obtains aluminum alloy plate materials;
Eight, cut off: use sawing machine to excise the defect part of aluminum alloy plate materials under room temperature condition, obtain the aluminum alloy plate materials that quality is homogeneous;
Nine, solution treatment and quenching: be use stove at the bottom of roller to carry out solution treatment under the condition of 475 DEG C in temperature by aluminum alloy plate materials homogeneous for quality, the treatment time is 2h, is then the quenching-in water 20s of 18 DEG C in temperature, obtains the aluminum alloy plate materials after quenching;
Ten, tension leveling: be carry out tension leveling by drawing die under the condition of 2.2% at stretching pass deformation rate by the aluminum alloy plate materials after quenching, obtain the aluminum alloy plate materials after stretching;
11, ageing treatment: by the aluminum alloy plate materials after stretching at temperature is 120 DEG C, insulation 6h, is then raised to 170 DEG C by temperature from 120 DEG C, and is be incubated 24h under the condition of 170 DEG C in temperature, obtains the aluminum alloy plate materials after ageing treatment;
12, saw is cut: the aluminum alloy plate materials after using sawing machine to cut saw ageing treatment under room temperature condition, obtains aviation aluminum alloy pre-stretching plate.
Test aviation aluminum alloy pre-stretching plate endwise tensile strength prepared by the present embodiment by GB/T228 " metallic substance room temperature tensile properties test method " and be not less than 510N/mm
2, Proof strength of non-proportional is not less than 441N/mm
2, elongation after fracture is not less than 10%; The transverse tensile strength of sheet material is not less than 510N/mm
2, Proof strength of non-proportional is not less than 441N/mm
2, elongation after fracture is not less than 9%; By GB/T4161 " metallic substance Plane Strain Fracture Toughness K
iCtest method " the longitudinal fracture toughness of testing aviation aluminum alloy pre-stretching plate prepared by the present embodiment is not less than 32N/mm
2.m
1/2, strength transverse rupture strength is not less than 27N/mm
2.m
1/2; The exfoliation Corrosion being tested aviation aluminum alloy pre-stretching plate prepared by the present embodiment by HB5455 " aluminium alloy breakaway corrosion test method " is not less than EB level; The C Zernike annular polynomial corrosive nature of aviation aluminum alloy pre-stretching plate prepared by the present embodiment is tested for adding 241N/mm by HB5259 " aluminum alloy C ring sample stress corrosion (cracking) test method "
2power 30 days is without any cracking phenomena; The conductivity value being tested aviation aluminum alloy pre-stretching plate prepared by the present embodiment by GB/T12966 " aluminium alloy Eddy Conductivity testing method " is not less than 22.0MS/m, test aviation aluminum alloy pre-stretching plate 100% flaw detection prepared by the present embodiment by ASTMB594 " ultrasonic testing of aviation alloyed aluminium converted products " and meet the requirement of A grade standard, be applicable to making aviation product.
Claims (8)
1. a manufacture method for aviation aluminum alloy pre-stretching plate, is characterized in that a kind of manufacture method of aviation aluminum alloy pre-stretching plate completes according to the following steps:
One, molten aluminium alloy is prepared: be first that aluminium takes aluminium ingot, copper ingot, magnesium ingot, zinc ingot metal, aluminium zirconium alloy ingot, aluminum titanium alloy ingot and aluminium Ti, B grain graining agent by massfraction 5.7% ~ 6.7%Zn, 1.9% ~ 2.6%Mg, 2.0% ~ 2.6%Cu, 0.08% ~ 0.15%Zr, 0.001% ~ 0.12%Si, 0.001% ~ 0.15%Fe, 0.001% ~ 0.1%Mn, 0.001% ~ 0.04%Cr, 0.001% ~ 0.06%Ti and surplus, then be melting 6h ~ 9h in the smelting furnace of 720 DEG C ~ 760 DEG C in temperature, obtain molten aluminium alloy;
Two, the side's of preparation ingot casting: being cast as thick at the molten aluminium alloy that casting temp is 705 DEG C ~ 730 DEG C, casting speed is 35mm/min ~ 45mm/min, step one obtains under be 10 DEG C ~ 20 DEG C and water coolant intensity being the condition of 0.01MPa ~ 0.05MPa by temperature of cooling water is 440mm and the wide square ingot casting for 1300mm;
Three, anneal: square ingot casting step 2 obtained is incubated 47h ~ 50h under temperature is the condition of 460 DEG C ~ 475 DEG C, naturally cool to room temperature after coming out of the stove and obtain the square ingot casting after annealing;
Four, prepare aluminum alloy square ingot casting: use planer that the square ingot casting after annealing is gone the casting oxide skin on surface under room temperature condition, obtaining thick is 380mm ~ 390mm and the wide aluminum alloy square ingot casting for 1250mm;
Five, prepare sheet material blank: use under room temperature condition sawing machine by thick be 1320mm for 380mm ~ 390mm and the wide aluminum alloy square ingot casting for 1250mm cut into length, thick be 380mm ~ 390mm and the wide sheet material blank for 1250mm;
Six, heat: temperature put into by sheet material blank step 5 obtained is that the resistance heading furnace of 375 DEG C ~ 420 DEG C heats, and heat-up time is 12h ~ 16h, obtains hot sheet blank;
Seven, aluminum alloy plate materials is prepared: hot sheet blank step 6 obtained uses mill milling under start rolling temperature is 380 DEG C ~ 420 DEG C and finishing temperature is the condition of 350 DEG C ~ 370 DEG C, obtains aluminum alloy plate materials;
Eight, cut off: use sawing machine to excise the defect part of aluminum alloy plate materials under room temperature condition, obtain the aluminum alloy plate materials that quality is homogeneous;
Nine, solution treatment and quenching: be use stove at the bottom of roller to carry out solution treatment under the condition of 475 DEG C in temperature by aluminum alloy plate materials homogeneous for quality, the treatment time is 2h, is then the quenching-in water 20s of 18 DEG C in temperature, obtains the aluminum alloy plate materials after quenching;
Ten, tension leveling: be carry out tension leveling by drawing die under the condition of 1.5% ~ 3% at stretching pass deformation rate by the aluminum alloy plate materials after quenching, obtain the aluminum alloy plate materials after stretching;
11, ageing treatment: by the aluminum alloy plate materials after stretching at temperature is 105 DEG C ~ 125 DEG C, insulation 4h ~ 8h, then temperature is raised to 165 DEG C ~ 175 DEG C from 105 DEG C ~ 125 DEG C, and be incubated 20h ~ 26h under the condition of 165 DEG C ~ 175 DEG C in temperature, obtain the aluminum alloy plate materials after ageing treatment;
12, saw is cut: the aluminum alloy plate materials after using sawing machine to cut saw ageing treatment under room temperature condition, obtains aviation aluminum alloy pre-stretching plate.
2. the manufacture method of a kind of aviation aluminum alloy pre-stretching plate according to claim 1, is characterized in that being cast as thick at the molten aluminium alloy that casting temp is 710 DEG C, casting speed is 40mm/min, step one obtains under be 16 DEG C and water coolant intensity being the condition of 0.02MPa by temperature of cooling water in step 2 is 440mm and the wide square ingot casting for 1300mm.
3. the manufacture method of a kind of aviation aluminum alloy pre-stretching plate according to claim 1, it is characterized in that square ingot casting step 2 obtained in step 3 is be incubated 48h under the condition of 470 DEG C in temperature, naturally cool to room temperature after coming out of the stove and obtain the square ingot casting after annealing.
4. the manufacture method of a kind of aviation aluminum alloy pre-stretching plate according to claim 1, it is characterized in that using under room temperature condition in step 5 sawing machine by thick be 1320mm for 380mm ~ 390mm and the wide aluminum alloy square ingot casting for 1250mm cut into length, thick be 385mm and the wide sheet material blank for 1250mm.
5. the manufacture method of a kind of aviation aluminum alloy pre-stretching plate according to claim 1, it is characterized in that temperature put into by sheet material blank step 5 obtained in step 6 is that the resistance heading furnace of 410 DEG C heats, heat-up time is 12h, obtains hot sheet blank.
6. the manufacture method of a kind of aviation aluminum alloy pre-stretching plate according to claim 1, it is characterized in that hot sheet blank step 6 obtained in step 7 uses mill milling under start rolling temperature is 400 DEG C and finishing temperature is the condition of 365 DEG C, obtain aluminum alloy plate materials.
7. the manufacture method of a kind of aviation aluminum alloy pre-stretching plate according to claim 1, it is characterized in that the aluminum alloy plate materials after quenching step 9 obtained in step 10 is carry out tension leveling by drawing die under the condition of 2.2% at stretching pass deformation rate, obtain the aluminum alloy plate materials after stretching.
8. the manufacture method of a kind of aviation aluminum alloy pre-stretching plate according to claim 1, it is characterized in that in step 11 by stretch after aluminum alloy plate materials at temperature is 120 DEG C, insulation 6h, then temperature is raised to 170 DEG C from 120 DEG C, and be incubated 24h under the condition of 170 DEG C in temperature, obtain the aluminum alloy plate materials after ageing treatment.
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| CN108672496B (en) * | 2018-05-16 | 2019-11-12 | 中铝东南材料院（福建）科技有限公司 | A kind of 6 be 7 be sheet alloy prestretching |
| CN110000214A (en) * | 2019-04-17 | 2019-07-12 | 河南永通铝业有限公司 | The production technology of high-performance pre-stretching aluminium sheet alternate product |
| CN110042333B (en) * | 2019-04-26 | 2020-12-29 | 东北轻合金有限责任公司 | Manufacturing method of 625 MPa-grade large-size aluminum alloy pre-stretched plate for aviation |
| CN115141990A (en) * | 2022-07-07 | 2022-10-04 | 南京工业大学 | Pretreatment method for improving baking hardenability of 6-series aluminum alloy for automobile body |
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| CN1834276A (en) * | 2006-04-25 | 2006-09-20 | 东北轻合金有限责任公司 | Method of preparing aviation alloyed aluminium variable section sheets |
| CN101037747A (en) * | 2007-04-29 | 2007-09-19 | 东北轻合金有限责任公司 | Aviation aluminum alloy pre-stretching plate and production method thereof |
| CN101037752A (en) * | 2007-04-29 | 2007-09-19 | 东北轻合金有限责任公司 | Aviation aluminum alloy pre-stretching plate and production method thereof |
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