CN105088113B - Method for manufacturing aluminum alloy free forge piece for spaceflight - Google Patents

Method for manufacturing aluminum alloy free forge piece for spaceflight Download PDF

Info

Publication number
CN105088113B
CN105088113B CN201510531569.5A CN201510531569A CN105088113B CN 105088113 B CN105088113 B CN 105088113B CN 201510531569 A CN201510531569 A CN 201510531569A CN 105088113 B CN105088113 B CN 105088113B
Authority
CN
China
Prior art keywords
temperature
forge piece
ingot
aluminum alloy
alloy
Prior art date
Application number
CN201510531569.5A
Other languages
Chinese (zh)
Other versions
CN105088113A (en
Inventor
刘平
吕新宇
刘洪雷
王英君
刘显东
丛福官
高新宇
李海仙
祁艳华
Original Assignee
东北轻合金有限责任公司
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by 东北轻合金有限责任公司 filed Critical 东北轻合金有限责任公司
Priority to CN201510531569.5A priority Critical patent/CN105088113B/en
Publication of CN105088113A publication Critical patent/CN105088113A/en
Application granted granted Critical
Publication of CN105088113B publication Critical patent/CN105088113B/en

Links

Abstract

The invention provides a method for manufacturing an aluminum alloy free forge piece for spaceflight and relates to a method for manufacturing an aluminum alloy free forge piece. The method aims to solve the technical problems that an existing aluminum alloy free forge piece cannot have high strength, high corrosion resistance and low density at the same time so that the requirements for high strength, corrosion resistance and light weight of aluminum alloy materials in the spaceflight field cannot be met. The method comprises the steps of 1, preparing an aluminum alloy solution; 2, manufacturing a round cast ingot; 3, carrying out dual-stage homogenizing annealing treatment; 4, manufacturing forge piece blank; 5, carrying out free forging; 6, performing solid-solution hardening treatment; 7, performing cold deformation treatment; and 8, performing two-stage aging treatment. The method has the advantages that by optimizing alloy components and adopting the optimized solid solution and aging processes after forging, the requirement for the overall performance of the aluminum alloy free forge piece is met; the manufactured aluminum alloy free forge piece is good in surface quality, the finished forge piece in industrial production is good in performance, and the overall mechanical property is good.

Description

A kind of manufacture method of space flight with aluminium alloy open die forgings

Technical field

The present invention relates to a kind of manufacture method of aluminium alloy open die forgings.

Background technology

Existing traditional high-strength/tenacity aluminum alloy, such as 7050 alloy of Al-Zn-Mg-Cu systems, strength and toughness are high but not anti-corrosion; Medium weldability aluminium alloy, such as Al-Zn-Mg systems 7005 and 7020 alloys, it is anti-corrosion but intensity is relatively low, cannot solve with high intensity While have high corrosion resisting property and density little problem, it is impossible to meet space industry high-strength to aluminum alloy materials, anti-corrosion, light The requirement of matter.

At present, China's a certain space flight a kind of open die forgings of product needed, it is desirable to which this kind of aluminium alloy open die forgings tension is strong Degree reaches 460N/mm2, Proof strength of non-proportional reach 420N/mm2, elongation after fracture reaches 8%, fracture toughness and is not less than 27MPa·m1/2, density be not more than 2.8g/cm3, stress corrosion performance it is molten in the NaCl that mass concentration is 3.5% in soaking at room temperature 0.75 σ is loaded in liquid0.2Rupture time is more than 100h, can meet space industry to new diseases requirement.

The content of the invention

The invention aims to solve aluminum current alloy free forging cannot and meanwhile there is high intensity and high corrosion resistance with And the problem that density is little, so as to meet, space industry is high-strength to aluminum alloy materials, anti-corrosion, lightweight requirement technology is asked Topic, and a kind of manufacture method of space flight aluminium alloy open die forgings is provided.

A kind of space flight of the present invention is carried out according to the following steps with the manufacture method of aluminium alloy open die forgings:

First, prepare aluminium alloy solution:According to mass percent Zn of element:5.5%~7.5%, Mg:1.5%~ 3.0%th, Cu:0.2%~0.55%, Zr:0.05%~0.18%, Si:≤ 0.10%, Fe:≤ 0.15%, Mn:0.2%~ 0.45%th, Cr:0.005%~0.1%, Ti:0.01%~0.05%, Sc:0.15%~0.45% and the ratio point of surplus Al Another name takes fine aluminium ingot, fine copper ingot, pure magnesium ingot, pure zinc ingot, aluminium-scandium alloy ingot, aluminum zircaloy ingot, aluminum titanium alloy ingot and aluminium titanium boron wire, Then melting 8h~10h under the conditions of temperature is for 740 DEG C~760 DEG C, obtains molten aluminium alloy;

2nd, prepare circle ingot casting:By the molten aluminium alloy obtained in step one temperature be 700 DEG C~750 DEG C, casting speed The bar that for 40mm/min~90mm/min, cooling water intensity be 0.03MPa~0.06MPa and cooling water temperature is 15 DEG C~35 DEG C Under part, the round ingot casting of a diameter of 170mm and length for 3500mm~5000mm is poured into;

3rd, two-step homogenization annealing:The round ingot casting that step 2 is obtained is carried out into two-step homogenization annealing, is obtained The round ingot casting of annealing;Described two-step homogenization annealing is specially:The round ingot casting that step 2 is obtained is 350 DEG C in temperature 8h~10h is incubated under conditions of~360 DEG C, is then warming up to 460 DEG C~470 DEG C from temperature for 350 DEG C~360 DEG C, in temperature For being incubated 18h~20h under conditions of 460 DEG C~470 DEG C, room temperature after coming out of the stove, is naturally cooled to;

4th, prepare forge piece blank reheating:The surface scale whole car of the round ingot casting of annealing step 3 obtained on lathe Ream, obtain the aluminium alloy round cast ingot of a diameter of 162mm, be then sawed into the forge piece blank reheating that length is 500mm;

5th, flat-die forging:The length that step 4 is obtained is 430 DEG C~450 DEG C for the forge piece blank reheating of 500mm in temperature 5h~7h is heated in resistance-heated furnace, 380 DEG C~400 DEG C are cooled to, and is then carried out under the conditions of temperature is for 380 DEG C~400 DEG C Three pulling flat-die forgings, obtain size for the vertical of (150mm~160mm) × (160mm~170mm) × (350mm~360mm) Cube forging;

6th, solid solution and Quenching Treatment:The size that step 5 is obtained is (150mm~160mm) × (160mm~170mm) The milling on milling machine of the cube forging of × (350mm~360mm) is (135mm~145mm) × (145mm~155mm) into size The cube open die forgings of × (335mm~345mm), in the salt bath furnace that temperature is 470 DEG C~480 DEG C be incubated 180min~ 200min, is transferred in the water that temperature is 30 DEG C~40 DEG C in 30s, and in the quenching-in water that temperature is 30 DEG C~40 DEG C, obtains Aluminum alloy forge piece to after quenching;

7th, cold deformation is processed:Aluminum alloy forge piece after the quenching obtained in step 6 is applied on 10,000 tons of forging machines 3%~5% deflection carries out deformation at room temperature process, obtains the aluminum alloy forge piece after deformation process;

8th, two-stage time effect is processed:The aluminum alloy forge piece that the cold deformation that step 7 is obtained is processed carries out two-stage time effect process; Described two-stage time effect is processed and is specially:The aluminum alloy forge piece that cold deformation that step 7 is obtained is processed temperature be 120 DEG C~ At 130 DEG C be incubated 6h~10h, be then warming up to 150 DEG C~160 DEG C from temperature for 120 DEG C~130 DEG C, temperature for 150 DEG C~ Under conditions of 160 DEG C be incubated 8h~10h, naturally cool to room temperature, on milling machine milling face into size be 130mm × 140mm × The aluminium alloy open die forgings of 330mm, obtains space flight aluminium alloy open die forgings.

Advantages of the present invention:

The present invention has reached aluminium alloy by optimized alloy composition using the solid solution and aging technique for optimizing after forging The combination property demand of open die forgings, the surface quality of the aluminium alloy open die forgings of preparation are good, finished product forging in commercial production Performance is good, and comprehensive mechanical property is excellent, by GB/T228《Metal material tensile testing at ambient temperature》Test T7452 states are certainly 460N/mm is more than by forging tensile strength2, Proof strength of non-proportional be more than 420N/mm2, elongation after fracture more than 8%, it is disconnected Toughness is split more than 27MPa m1/2;By GB/T 22640《The ring specimen stress corrosion (cracking) test method of aluminium alloy converted productss》 The stress corrosion performance of test T7452 state aluminium alloy open die forgings is in soaking at room temperature in the NaCl solution that mass concentration is 3.5% 0.75 σ of middle loading0.2Rupture time is more than 100h;Density is less than 2.8g/cm3

Specific embodiment

Specific embodiment one:Present embodiment is a kind of manufacture method of space flight aluminium alloy open die forgings, specifically Carry out according to the following steps:

First, prepare aluminium alloy solution:According to mass percent Zn of element:5.5%~7.5%, Mg:1.5%~ 3.0%th, Cu:0.2%~0.55%, Zr:0.05%~0.18%, Si:≤ 0.10%, Fe:≤ 0.15%, Mn:0.2%~ 0.45%th, Cr:0.005%~0.1%, Ti:0.01%~0.05%, Sc:0.15%~0.45% and the ratio point of surplus Al Another name takes fine aluminium ingot, fine copper ingot, pure magnesium ingot, pure zinc ingot, aluminium-scandium alloy ingot, aluminum zircaloy ingot, aluminum titanium alloy ingot and aluminium titanium boron wire, Then melting 8h~10h under the conditions of temperature is for 740 DEG C~760 DEG C, obtains molten aluminium alloy;

2nd, prepare circle ingot casting:By the molten aluminium alloy obtained in step one temperature be 700 DEG C~750 DEG C, casting speed The bar that for 40mm/min~90mm/min, cooling water intensity be 0.03MPa~0.06MPa and cooling water temperature is 15 DEG C~35 DEG C Under part, the round ingot casting of a diameter of 170mm and length for 3500mm~5000mm is poured into;

3rd, two-step homogenization annealing:The round ingot casting that step 2 is obtained is carried out into two-step homogenization annealing, is obtained The round ingot casting of annealing;Described two-step homogenization annealing is specially:The round ingot casting that step 2 is obtained is 350 DEG C in temperature 8h~10h is incubated under conditions of~360 DEG C, is then warming up to 460 DEG C~470 DEG C from temperature for 350 DEG C~360 DEG C, in temperature For being incubated 18h~20h under conditions of 460 DEG C~470 DEG C, room temperature after coming out of the stove, is naturally cooled to;

4th, prepare forge piece blank reheating:The surface scale whole car of the round ingot casting of annealing step 3 obtained on lathe Ream, obtain the aluminium alloy round cast ingot of a diameter of 162mm, be then sawed into the forge piece blank reheating that length is 500mm;

5th, flat-die forging:The length that step 4 is obtained is 430 DEG C~450 DEG C for the forge piece blank reheating of 500mm in temperature 5h~7h is heated in resistance-heated furnace, 380 DEG C~400 DEG C are cooled to, and is then carried out under the conditions of temperature is for 380 DEG C~400 DEG C Three pulling flat-die forgings, obtain size for the vertical of (150mm~160mm) × (160mm~170mm) × (350mm~360mm) Cube forging;

6th, solid solution and Quenching Treatment:The size that step 5 is obtained is (150mm~160mm) × (160mm~170mm) The milling on milling machine of the cube forging of × (350mm~360mm) is (135mm~145mm) × (145mm~155mm) into size The cube open die forgings of × (335mm~345mm), in the salt bath furnace that temperature is 470 DEG C~480 DEG C be incubated 180min~ 200min, is transferred in the water that temperature is 30 DEG C~40 DEG C in 30s, and in the quenching-in water that temperature is 30 DEG C~40 DEG C, obtains Aluminum alloy forge piece to after quenching;

7th, cold deformation is processed:Aluminum alloy forge piece after the quenching obtained in step 6 is applied on 10,000 tons of forging machines 3%~5% deflection carries out deformation at room temperature process, obtains the aluminum alloy forge piece after deformation process;

8th, two-stage time effect is processed:The aluminum alloy forge piece that the cold deformation that step 7 is obtained is processed carries out two-stage time effect process; Described two-stage time effect is processed and is specially:The aluminum alloy forge piece that cold deformation that step 7 is obtained is processed temperature be 120 DEG C~ At 130 DEG C be incubated 6h~10h, be then warming up to 150 DEG C~160 DEG C from temperature for 120 DEG C~130 DEG C, temperature for 150 DEG C~ Under conditions of 160 DEG C be incubated 8h~10h, naturally cool to room temperature, on milling machine milling face into size be 130mm × 140mm × The aluminium alloy open die forgings of 330mm, obtains space flight aluminium alloy open die forgings.

Specific embodiment two:Difference of the present embodiment from specific embodiment one is:Fine aluminium described in step one The purity of ingot is more than 99.7%.Other are identical with specific embodiment one.

Specific embodiment three:Difference of the present embodiment from specific embodiment one or two is:Described in step In aluminium titanium boron wire, the mass fraction of titanium is 5%, and the mass fraction of boron is 0.2%, and remaining is aluminum.Other and specific embodiment one Or two is identical.

Specific embodiment four:Difference of the present embodiment from specific embodiment one to three is:Will step in step 2 The molten aluminium alloy obtained in rapid one temperature be 750 DEG C, casting speed be 60mm/min, cooling water intensity be 0.06MPa and Under conditions of cooling water temperature is 25 DEG C, the round ingot casting of a diameter of 170mm and length for 3500mm is poured into.Other and concrete reality Apply mode one to three identical.

Specific embodiment five:Difference of the present embodiment from specific embodiment one to four is:Will step in step 3 The rapid two round ingot castings for obtaining carry out two-step homogenization annealing, obtain the round ingot casting annealed;Described two-step homogenization annealing Process is specially:The round ingot casting that step 2 is obtained temperature be 360 DEG C under conditions of be incubated 10h, then from temperature be 360 DEG C 470 DEG C are warming up to, and 20h are incubated under conditions of temperature is for 470 DEG C, are naturally cooled to room temperature after coming out of the stove.Other be embodied as Mode one to four is identical.

Specific embodiment six:Difference of the present embodiment from specific embodiment one to five is:Described in step 6 The heating medium of salt bath furnace is made up of for 75% sodium nitrate the potassium nitrate and mass fraction that mass fraction is 25%.Other with it is concrete Embodiment one to five is identical.

Specific embodiment seven:Difference of the present embodiment from specific embodiment one to six is:Described in step 8 Two-stage time effect process be specially:The aluminum alloy forge piece that the cold deformation that step 7 is obtained is processed is to be incubated at 130 DEG C in temperature 8h, is then warming up to 160 DEG C from temperature for 130 DEG C, is incubated 10h, naturally cools to room temperature under conditions of temperature is for 160 DEG C, On milling machine, milling face is the aluminium alloy open die forgings of 130mm × 140mm × 330mm into size, obtains space flight aluminium alloy freedom Forging.Other are identical with specific embodiment one to six.

Beneficial effects of the present invention are verified by tests below:

Test one:This test is a kind of manufacture method of space flight aluminium alloy open die forgings, is specifically entered according to the following steps Capable:

First, prepare aluminium alloy solution:According to mass percent Zn of element:6.3%th, Mg:2.2%th, Cu:0.4%th, Zr: 0.1%th, Si:0.05%th, Fe:0.08%th, Mn:0.3%th, Cr:0.05%th, Ti:0.03%th, Sc:0.28% and the ratio of surplus Al Example weighs fine aluminium ingot, fine copper ingot, pure magnesium ingot, pure zinc ingot, aluminium-scandium alloy ingot, aluminum zircaloy ingot, aluminum titanium alloy ingot and aluminum titanium respectively Boron filament, then the melting 9h under the conditions of temperature is for 750 DEG C, obtains molten aluminium alloy;

2nd, prepare circle ingot casting:By the molten aluminium alloy obtained in step one temperature be 725 DEG C, casting speed be 65mm/ Under conditions of min, cooling water intensity are 0.035MPa and cooling water temperature is 25 DEG C, pour into a diameter of 170mm and length is The round ingot casting of 5000mm;

3rd, two-step homogenization annealing:The round ingot casting that step 2 is obtained is carried out into two-step homogenization annealing, is obtained The round ingot casting of annealing;Described two-step homogenization annealing is specially:The round ingot casting that step 2 is obtained is 355 DEG C in temperature Under conditions of be incubated 10h, be then warming up to 465 DEG C from temperature for 355 DEG C, temperature be 465 DEG C under conditions of be incubated 18h, go out Furnace rear naturally cools to room temperature;

4th, prepare forge piece blank reheating:The surface scale whole car of the round ingot casting of annealing step 3 obtained on lathe Ream, obtain the aluminium alloy round cast ingot of a diameter of 162mm, be then sawed into the forge piece blank reheating that length is 500mm;

5th, flat-die forging:The length that step 4 is obtained adds in the resistance that temperature is 440 DEG C for the forge piece blank reheating of 500mm 6h is heated in hot stove, 390 DEG C are cooled to, and then three pulling flat-die forgings is carried out under the conditions of temperature is for 390 DEG C, is obtained size For the cube forging of 150mm × 160mm × 350mm;

6th, solid solution and Quenching Treatment:Cube forging of the size that step 5 is obtained for 150mm × 160mm × 350mm On milling machine milling into size for 135mm × 145mm × 335mm cube open die forgings, in the salt bath furnace that temperature is 470 DEG C Insulation 180min, is transferred in the water that temperature is 35 DEG C in 30s, and in the quenching-in water that temperature is 35 DEG C, after being quenched Aluminum alloy forge piece;

7th, cold deformation is processed:Aluminum alloy forge piece after the quenching obtained in step 6 is applied on 10,000 tons of forging machines 4% deflection carries out deformation at room temperature process, obtains the aluminum alloy forge piece after deformation process;

8th, two-stage time effect is processed:The aluminum alloy forge piece that the cold deformation that step 7 is obtained is processed carries out two-stage time effect process; Described two-stage time effect is processed and is specially:The aluminum alloy forge piece that the cold deformation that step 7 is obtained is processed is at 120 DEG C in temperature Insulation 8h, is then warming up to 150 DEG C from temperature for 120 DEG C, is incubated 8h, naturally cools to room under conditions of temperature is for 150 DEG C Temperature, on milling machine, milling face is the aluminium alloy open die forgings of 130mm × 140mm × 330mm into size, obtains space flight aluminium alloy certainly By forging.

The purity of the fine aluminium ingot described in step one is more than 99.7%;The mass fraction of titanium in aluminium titanium boron wire described in step one For 5%, the mass fraction of boron is 0.2%, and remaining is aluminum;The heating medium of the salt bath furnace described in step 6 by mass fraction is 25% potassium nitrate and mass fraction are constituted for 75% sodium nitrate.

The space flight that this test is obtained passes through GB/T228 with aluminium alloy open die forgings《Metal material tensile testing at ambient temperature》 Test T7452 state forging tensile strength is 515N/mm2, Proof strength of non-proportional be 480N/mm2, elongation after fracture be 12%th, fracture toughness is 36MPa m1/2;By GB/T 22640《The ring specimen stress corrosion (cracking) test of aluminium alloy converted productss Method》The stress corrosion performance of test T7452 state aluminum alloy forge pieces, soaking at room temperature is in 3.5%NaCl solution and loads 360N/ mm2Stress condition under, sample is still unbroken after 600h;Density is 2.78g/cm3

Space flight aluminium alloy open die forgings prepared by this test can be answered as space flight T7452 state aluminium alloys open die forgings With.

Claims (1)

1. a kind of manufacture method of space flight with aluminium alloy open die forgings, it is characterised in that manufacture of the space flight with aluminium alloy open die forgings Method is carried out according to the following steps:
First, prepare aluminium alloy solution:According to mass percent Zn of element:6.3%th, Mg:2.2%th, Cu:0.4%th, Zr: 0.1%th, Si:0.05%th, Fe:0.08%th, Mn:0.3%th, Cr:0.05%th, Ti:0.03%th, Sc:0.28% and the ratio of surplus Al Example weighs fine aluminium ingot, fine copper ingot, pure magnesium ingot, pure zinc ingot, aluminium-scandium alloy ingot, aluminum zircaloy ingot, aluminum titanium alloy ingot and aluminum titanium respectively Boron filament, then the melting 9h under the conditions of temperature is for 750 DEG C, obtains molten aluminium alloy;
2nd, prepare circle ingot casting:By the molten aluminium alloy obtained in step one temperature be 725 DEG C, casting speed be 65mm/min, Under conditions of cooling water intensity is 0.035MPa and cooling water temperature is 25 DEG C, pours into a diameter of 170mm and length is The round ingot casting of 5000mm;
3rd, two-step homogenization annealing:The round ingot casting that step 2 is obtained is carried out into two-step homogenization annealing, is annealed Round ingot casting;Described two-step homogenization annealing is specially:The round ingot casting that step 2 is obtained is in the bar that temperature is 355 DEG C 10h is incubated under part, then 465 DEG C is warming up to from temperature for 355 DEG C, is incubated 18h, after coming out of the stove under conditions of temperature is for 465 DEG C Naturally cool to room temperature;
4th, prepare forge piece blank reheating:The surface scale whole turning of the round ingot casting of the annealing on lathe obtaining step 3 is fallen, The aluminium alloy round cast ingot of a diameter of 162mm is obtained, the forge piece blank reheating that length is 500mm is then sawed into;
5th, flat-die forging:The length that step 4 is obtained is the forge piece blank reheating of 500mm in the resistance-heated furnace that temperature is 440 DEG C Middle heating 6h, is cooled to 390 DEG C, then carries out three pulling flat-die forgings under the conditions of temperature is for 390 DEG C, and obtaining size is The cube forging of 150mm × 160mm × 350mm;
6th, solid solution and Quenching Treatment:The size that step 5 is obtained is the cube forging of 150mm × 160mm × 350mm in milling On bed, milling is the cube open die forgings of 135mm × 145mm × 335mm into size, is incubated in the salt bath furnace that temperature is 470 DEG C 180min, is transferred in the water that temperature is 35 DEG C in 30s, and in the quenching-in water that temperature is 35 DEG C, the aluminum after being quenched Alloy forged piece;
7th, cold deformation is processed:The aluminum alloy forge piece after the quenching obtained in step 6 is applied 4% on 10,000 tons of forging machines to become Shape amount carries out deformation at room temperature process, obtains the aluminum alloy forge piece after deformation process;
8th, two-stage time effect is processed:The aluminum alloy forge piece that the cold deformation that step 7 is obtained is processed carries out two-stage time effect process;It is described Two-stage time effect process be specially:The aluminum alloy forge piece that the cold deformation that step 7 is obtained is processed is to be incubated at 120 DEG C in temperature 8h, is then warming up to 150 DEG C from temperature for 120 DEG C, is incubated 8h, naturally cools to room temperature under conditions of temperature is for 150 DEG C, On milling machine, milling face is the aluminium alloy open die forgings of 130mm × 140mm × 330mm into size, obtains space flight aluminium alloy open die forging Part;
The purity of the fine aluminium ingot described in step one is more than 99.7%;In aluminium titanium boron wire described in step one, the mass fraction of titanium is 5%, the mass fraction of boron is 0.2%, and remaining is aluminum;The heating medium of the salt bath furnace described in step 6 is 25% by mass fraction Potassium nitrate and mass fraction be 75% sodium nitrate composition.
CN201510531569.5A 2015-08-27 2015-08-27 Method for manufacturing aluminum alloy free forge piece for spaceflight CN105088113B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201510531569.5A CN105088113B (en) 2015-08-27 2015-08-27 Method for manufacturing aluminum alloy free forge piece for spaceflight

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN201510531569.5A CN105088113B (en) 2015-08-27 2015-08-27 Method for manufacturing aluminum alloy free forge piece for spaceflight

Publications (2)

Publication Number Publication Date
CN105088113A CN105088113A (en) 2015-11-25
CN105088113B true CN105088113B (en) 2017-03-22

Family

ID=54569431

Family Applications (1)

Application Number Title Priority Date Filing Date
CN201510531569.5A CN105088113B (en) 2015-08-27 2015-08-27 Method for manufacturing aluminum alloy free forge piece for spaceflight

Country Status (1)

Country Link
CN (1) CN105088113B (en)

Families Citing this family (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN107159830A (en) * 2017-07-20 2017-09-15 山东南山铝业股份有限公司 Forging method
CN107964615A (en) * 2017-11-22 2018-04-27 华南理工大学 A kind of extrudate high-strength 7xxx line aluminium alloys and preparation method thereof
CN108103371B (en) * 2017-12-15 2019-06-18 东北轻合金有限责任公司 A kind of high-performance space flight fastener aluminium alloy wires production method
CN108642348B (en) * 2018-06-05 2020-06-16 湖南东方钪业股份有限公司 Al-Zn-Mg series aluminum alloy section and preparation method thereof
CN108456812B (en) * 2018-06-29 2020-02-18 中南大学 Low-Sc high-strength high-toughness high-hardenability aluminum-zinc-magnesium alloy and preparation method thereof
CN109136689B (en) * 2018-10-22 2019-09-10 广西平果百矿高新铝业有限公司 A kind of Al-Zn-Mg-Cu ultra-high-strength aluminum alloy and its crushing failure at high speed press quenching production method
CN109570230A (en) * 2018-11-14 2019-04-05 中国航空工业集团公司西安飞机设计研究所 The forming method and equipment of aluminum alloy junction component
CN109338257A (en) * 2018-12-20 2019-02-15 西南铝业(集团)有限责任公司 A kind of method of aluminum alloy forge piece and the uniformity for improving aluminum alloy forge piece
CN109732023A (en) * 2018-12-27 2019-05-10 桂林理工大学 A method of control Al-alloy casing isothermal precision forging process size rebound
CN109666827A (en) * 2019-02-22 2019-04-23 洛阳华陵镁业有限公司 A kind of super-strong and super-toughened 7055Sc aluminum alloy forge piece
CN110284029B (en) * 2019-07-26 2020-10-20 福建祥鑫股份有限公司 Aluminum alloy for main frame structure of transmission tower and preparation method thereof
CN110423924B (en) * 2019-08-15 2020-06-09 江苏裕隆锻造有限公司 Forging and heat treatment process of free forging

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN1489637A (en) * 2000-12-21 2004-04-14 阿尔科公司 Aluminum alloy products and artificial aging method
JP5231223B2 (en) * 2005-07-21 2013-07-10 アレリス、アルミナム、コブレンツ、ゲゼルシャフト、ミット、ベシュレンクテル、ハフツングAleris Aluminum Koblenz Gmbh Forged aluminum AA7000 series alloy product and method for producing the product
RU2473710C2 (en) * 2006-06-30 2013-01-27 КОНСТЕЛЛИУМ РОЛЛД ПРОДАКТС - РЕЙВЕНСВУД ЭлЭлСи High-strength heat-treatable aluminium alloy
US8002913B2 (en) * 2006-07-07 2011-08-23 Aleris Aluminum Koblenz Gmbh AA7000-series aluminum alloy products and a method of manufacturing thereof
CN102732761B (en) * 2012-06-18 2014-01-08 中国航空工业集团公司北京航空材料研究院 7000 series aluminum alloy material and preparation method thereof
CN104745985A (en) * 2013-12-25 2015-07-01 青岛玉光精铸厂 Heat treatment technology of 7050 high-strength aluminum alloy forge piece
CN104099542B (en) * 2014-08-11 2016-05-04 贵州航天新力铸锻有限责任公司 The heat treatment method of aluminium alloy heavy forging
CN104178711A (en) * 2014-08-21 2014-12-03 东北轻合金有限责任公司 Manufacturing method for aerospace aluminum alloy board

Also Published As

Publication number Publication date
CN105088113A (en) 2015-11-25

Similar Documents

Publication Publication Date Title
CN102108463B (en) Aluminium alloy product suitable for manufacturing structures and preparation method
CN101484603B (en) Aa7000-series aluminium alloy products and a method of manufacturing thereof
CN104018041B (en) A kind of high ferro car body aluminium section bar and preparation method thereof
KR101148421B1 (en) Aluminum alloy forgings and process for production thereof
CN105838945B (en) A kind of superpower high-ductility corrosion aluminium alloy of anti-recrystallizing and preparation method thereof
CN1325682C (en) Al-cu alloy with high toughness
CN102978488B (en) Production technology of aluminum alloy sectional bar for automobile bumper
CN101896631B (en) Al-Mg-Zn wrought alloy product and manufacture method thereof
CN104805319B (en) Manufacturing method for 2xxx series ultra-large-dimension aluminum alloy round ingot
JP2013227652A (en) Aluminum alloy forged material for automobile and method for manufacturing the same
CN102796925B (en) High-strength die-casting aluminum alloy for pressure casting
CN101914710B (en) Manufacture method of aluminum alloy sheet for high-speed train structure
CN102839297B (en) High-temperature titanium alloy and preparation method thereof
CN102513479B (en) Production process for large-diameter fine isometric crystal tissue titanium alloy bar
CN102876940B (en) Manufacturing method of aluminum alloy thin plate with stable performance
CN102962425B (en) Preparation method of oblique oil cylinder body
CN1233862C (en) Hypereutectic silicon-aluminium alloy material and its production method
RU2463371C2 (en) Magnesium-containing high-silica aluminium alloys used as structural materials and method of their manufacturing
CN102066596B (en) There is the Al-Zn-Mg alloy product of the quenching sensitive of reduction
CN104357690B (en) The preparation technology of strong anti-corrosion high Mg-Al alloy plate in a kind of
US6790407B2 (en) High-strength alloy based on aluminium and a product made of said alloy
US20150316210A1 (en) Aluminum alloy material for high-pressure hydrogen gas container and method for producing the same
CN103103372A (en) Smelting preparation method for anti-stamping aluminum alloy section bar
CN102943193B (en) Grain refinement machining process of hard aluminium alloy cast ingot
CN103882271B (en) A kind of high-strength high-elongation ratio Al-Mg-Si-Cu alloy material and preparation method thereof

Legal Events

Date Code Title Description
PB01 Publication
C06 Publication
SE01 Entry into force of request for substantive examination
C10 Entry into substantive examination
GR01 Patent grant
C14 Grant of patent or utility model
TR01 Transfer of patent right

Effective date of registration: 20171024

Address after: 150069 Heilongjiang city of Harbin province Pingfang District haping Road No. 8

Patentee after: Harbin East Light Special Material Co., Ltd.

Address before: 150060 Xinjiang, Harbin cottage area, No. three street, No. 11, No.

Patentee before: Dongbei Light Alloy Co., Ltd.

TR01 Transfer of patent right