CN108165848A - A kind of manufacturing method of aviation alloyed aluminium section bar - Google Patents
A kind of manufacturing method of aviation alloyed aluminium section bar Download PDFInfo
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- CN108165848A CN108165848A CN201611117734.3A CN201611117734A CN108165848A CN 108165848 A CN108165848 A CN 108165848A CN 201611117734 A CN201611117734 A CN 201611117734A CN 108165848 A CN108165848 A CN 108165848A
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C1/00—Making non-ferrous alloys
- C22C1/02—Making non-ferrous alloys by melting
- C22C1/026—Alloys based on aluminium
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C1/00—Making non-ferrous alloys
- C22C1/02—Making non-ferrous alloys by melting
- C22C1/03—Making non-ferrous alloys by melting using master alloys
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C21/00—Alloys based on aluminium
- C22C21/10—Alloys based on aluminium with zinc as the next major constituent
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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
- C22F1/053—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 zinc as the next major constituent
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Abstract
A kind of manufacturing method of aviation alloyed aluminium section bar, the present invention relates to the manufacturing methods of aluminium alloy extrusions.The present invention is to solve the problem of all kinds of aluminium alloy extrusions tensile strength of prior art production, Proof strength of non-proportional, low elongation after fracture and exfoliation Corrosion.Method：First, melting；2nd, it casts；3rd, it cuts off；4th, railway carriage；5th, it anneals；6th, it heats；7th, it squeezes；8th, it is dissolved water quenching；9th, it stretches；Tenth, timeliness.The present invention passes through optimized alloy ingredient, the solid solution using optimization and aging technique, have reached comprehensive performance demand of the user to this alloy profile, the aluminium alloy extrusions entity size of preparation, surface quality are good after squeezing, processability is good in industrial production, and comprehensive mechanical property is excellent.The present invention is used to prepare aviation alloyed aluminium section bar.
Description
Technical field
The present invention relates to the manufacturing methods of aluminium alloy extrusions.
Background technology
Aluminum alloy materials use scope is wide, industrially can be applied to building, electronic apparatus, transport, Aeronautics and Astronautics etc.
Every field.At present, a certain aviation in China needs a kind of special section bar with product, it is desirable that such 74511 state section bar of aluminum alloy T
Tensile strength reaches 540N/mm2, Proof strength of non-proportional reach 480N/mm2, elongation after fracture reach 8%, Peeling Corrosion
Performance reaches EB grades.
It is entitled in being studied in this field《A kind of manufacturing method of space flight aluminium alloy rivet bar》Disclose one
The method that kind prepares aluminium alloy as main composition using copper using single-stage aging；It is entitled《A kind of large-size aluminum alloy ingot
Preparation method》A kind of preparation method of aluminium alloy cast ingot is disclosed, but all kinds of aluminium alloy extrusions tensions of prior art production are strong
Degree, Proof strength of non-proportional, elongation after fracture and exfoliation Corrosion are low, therefore the application that can not meet aviation articles for use will
It asks.
Invention content
All kinds of aluminium alloy extrusions tensile strength, regulation Non-proportional extension the present invention is to solve prior art production are strong
Degree, the problem of elongation after fracture and exfoliation Corrosion are low, and provide and a kind of aviation alloyed aluminium type is manufactured using two-stage time effect
The method of material.
A kind of method using two-stage time effect manufacture aviation alloyed aluminium section bar is specifically prepared according to following steps：
First, melting：It is Zn by the mass percent of element：5.9%~6.9%, Mg：2.0%~2.7%, Cu：1.9%~
2.5%th, Zr：0.08%~0.15%, Si：≤ 0.12%, Fe：≤ 0.15%, Mn：≤ 0.10%, Cr：≤ 0.04%, Ti：≤
0.06% and surplus weigh fine aluminium ingot, fine copper ingot, pure magnesium ingot, pure zinc ingot, aluminium zircaloy ingot, aluminum titanium alloy ingot and aluminium titanium boron for Al
Grain refiner is simultaneously added in dry smelting furnace, and melting 6h~7h under the conditions of being 720 DEG C~760 DEG C in temperature obtains aluminium
Alloy molten solution；
2nd, it casts：By the aluminium alloy solution that step 1 obtains temperature be 715 DEG C~750 DEG C, casting speed be 80mm/min~
90mm/min, cooling water intensity are 0.01MPa~0.03MPa, cooling water temperature is cast as directly under conditions of being 18 DEG C~25 DEG C
Diameter is the casting rod of 192mm~195mm；
3rd, it cuts off：The casting rod that step 2 obtains is cut into the stub that length is 400mm~450mm；
4th, railway carriage：The stub vehicle that step 3 obtains is gone to the oxide skin on surface, obtains aluminium alloy cast ingot；
5th, it anneals：It is carried out under conditions of being 460 DEG C~475 DEG C in annealing temperature by the aluminium alloy cast ingot that step 4 obtains uniform
Annealing 31h~33h；
6th, it heats：Aluminium alloy cast ingot after step 5 is annealed is put into resistance-heated furnace, and aluminium alloy cast ingot is heated to 380
DEG C~410 DEG C, the aluminium alloy cast ingot that obtains that treated；
7th, it squeezes：Step 6 treated aluminium alloy cast ingot milling is squeezed by section mould for aluminium alloy, extrusion temperature 380
DEG C~400 DEG C, obtain the aluminium alloy extrusions that length is 10000mm~10100mm；
8th, it is dissolved water quenching：It is dissolved, protects under the conditions of being 465 DEG C~475 DEG C in temperature by the aluminium alloy extrusions that step 7 obtains
It comes out of the stove after warm 1h~1.2h water quenching；
9th, it stretches：Step 8 is dissolved aluminium alloy extrusions tension straingtening in 4h after water quenching, control drawing deformation is
1.5%~3.0%；
Tenth, timeliness：The aluminium alloy extrusions of step 9 tension straingtening is subjected to two-stage time effect, wherein, first order timeliness is heated to temperature
It is 120 DEG C~125 DEG C to spend, and keeps the temperature 4h~5h, and it is 160 DEG C~170 DEG C that second level timeliness, which is heated to temperature, keeps the temperature 11h~13h,
Aviation alloyed aluminium section bar is prepared.
For impurity Si less than 0.12%, Fe less than 0.15%, other are single in aviation alloyed aluminium section bar prepared by the present invention
Impurity is less than 0.05%, and the impurity in the range of this does not influence the performance of aluminium alloy extrusions.
The beneficial effects of the invention are as follows：The present invention by optimized alloy ingredient, after squeezing using the solid solution of optimization and when
Effect technique has reached comprehensive performance demand of the user to this alloy profile, the aluminium alloy extrusions entity size of preparation, surface quality
Well, processability is good in industrial production, and comprehensive mechanical property is excellent, passes through GB/T228《Metal material room temperature draws experiment side
Method》It tests T74511 state section bars tensile strength and is not less than 540N/mm2, Proof strength of non-proportional be not less than 480N/mm2、
Elongation after fracture is not less than 8%；Pass through HB 5455《Aluminium alloy breakaway corrosion test method》Test the stripping of T74511 state section bars
Corrosive nature is fallen not less than EB grades.It is suitble to make aviation alloyed aluminium section bar.
The present invention is used to prepare aviation alloyed aluminium section bar.
Specific embodiment
Technical solution of the present invention is not limited to the specific embodiment of act set forth below, further include each specific embodiment it
Between arbitrary combination.
Specific embodiment one：A kind of method using two-stage time effect manufacture aviation alloyed aluminium section bar of present embodiment,
Specifically prepared according to following steps：
First, melting：It is Zn by the mass percent of element：5.9%~6.9%, Mg：2.0%~2.7%, Cu：1.9%~
2.5%th, Zr：0.08%~0.15%, Si：≤ 0.12%, Fe：≤ 0.15%, Mn：≤ 0.10%, Cr：≤ 0.04%, Ti：≤
0.06% and surplus weigh fine aluminium ingot, fine copper ingot, pure magnesium ingot, pure zinc ingot, aluminium zircaloy ingot, aluminum titanium alloy ingot and aluminium titanium boron for Al
Grain refiner is simultaneously added in dry smelting furnace, and melting 6h~7h under the conditions of being 720 DEG C~760 DEG C in temperature obtains aluminium
Alloy molten solution；
2nd, it casts：By the aluminium alloy solution that step 1 obtains temperature be 715 DEG C~750 DEG C, casting speed be 80mm/min~
90mm/min, cooling water intensity are 0.01MPa~0.03MPa, cooling water temperature is cast as directly under conditions of being 18 DEG C~25 DEG C
Diameter is the casting rod of 192mm~195mm；
3rd, it cuts off：The casting rod that step 2 obtains is cut into the stub that length is 400mm~450mm；
4th, railway carriage：The stub vehicle that step 3 obtains is gone to the oxide skin on surface, obtains aluminium alloy cast ingot；
5th, it anneals：It is carried out under conditions of being 460 DEG C~475 DEG C in annealing temperature by the aluminium alloy cast ingot that step 4 obtains uniform
Annealing 31h~33h；
6th, it heats：Aluminium alloy cast ingot after step 5 is annealed is put into resistance-heated furnace, and aluminium alloy cast ingot is heated to 380
DEG C~410 DEG C, the aluminium alloy cast ingot that obtains that treated；
7th, it squeezes：Step 6 treated aluminium alloy cast ingot milling is squeezed by section mould for aluminium alloy, extrusion temperature 380
DEG C~400 DEG C, obtain the aluminium alloy extrusions that length is 10000mm~10100mm；
8th, it is dissolved water quenching：It is dissolved, protects under the conditions of being 465 DEG C~475 DEG C in temperature by the aluminium alloy extrusions that step 7 obtains
It comes out of the stove after warm 1h~1.2h water quenching；
9th, it stretches：Step 8 is dissolved aluminium alloy extrusions tension straingtening in 4h after water quenching, control drawing deformation is
1.5%~3.0%；
Tenth, timeliness：The aluminium alloy extrusions of step 9 tension straingtening is subjected to two-stage time effect, wherein, first order timeliness is heated to temperature
It is 120 DEG C~125 DEG C to spend, and keeps the temperature 4h~5h, and it is 160 DEG C~170 DEG C that second level timeliness, which is heated to temperature, keeps the temperature 11h~13h,
Aviation alloyed aluminium section bar is prepared.
Present embodiment is by optimized alloy ingredient, and the solid solution using optimization and aging technique, have reached use after squeezing
Family is to the comprehensive performance demand of this alloy profile, and the aluminium alloy extrusions entity size of preparation, surface quality are good, in industrial production
Processability is good, and comprehensive mechanical property is excellent, passes through GB/T228《Metal material room temperature draws test method》Test T74511 states
Section bar tensile strength is not less than 540N/mm2, Proof strength of non-proportional be not less than 480N/mm2, elongation after fracture is not less than
8%；Pass through HB 5455《Aluminium alloy breakaway corrosion test method》The exfoliation Corrosion of experiment T74511 state section bars is not less than
EB grades.It is suitble to make aviation alloyed aluminium section bar.
Specific embodiment two：The present embodiment is different from the first embodiment in that：The matter of element is pressed in step 1
Amount percentage is Zn：6.2%~6.5%, Mg：2.2%~2.5%, Cu：2.0%~2.2%, Zr：0.09%~0.12%,
Si：≤ 0.10%, Fe：≤ 0.12%, Mn：≤ 0.06%, Cr：≤ 0.03%, Ti：≤ 0.05% and surplus weigh fine aluminium for Al
Ingot, fine copper ingot, pure magnesium ingot, pure zinc ingot, aluminium zircaloy ingot, aluminum titanium alloy ingot and aluminium Ti, B grain graining agent are simultaneously added to dry
In smelting furnace.It is other same as the specific embodiment one.
Specific embodiment three：The present embodiment is different from the first and the second embodiment in that：Element is pressed in step 1
Mass percent be Zn：6.4%th, Mg：2.3%th, Cu：2.1%th, Zr：0.10%th, Si：0.05%th, Fe：0.08%th, Mn：
0.05%th, Cr：0.02%th, Ti：0.03% and surplus weigh fine aluminium ingot, fine copper ingot, pure magnesium ingot, pure zinc ingot, aluminium zircaloy for Al
Ingot, aluminum titanium alloy ingot and aluminium Ti, B grain graining agent are simultaneously added in dry smelting furnace.It is other with specific embodiment one or
Two is identical.
Specific embodiment four：Unlike one of present embodiment and specific embodiment one to three：In step 1
Temperature is melting under the conditions of 730 DEG C.It is other identical with one of specific embodiment one to three.
Specific embodiment five：Unlike one of present embodiment and specific embodiment one to four：In step 2
Temperature is 720 DEG C, casting speed 85mm/min, cooling water intensity are 0.02MPa, cooling water temperature is cast under conditions of being 19 DEG C
It makes.It is other identical with one of specific embodiment one to four.
Specific embodiment six：Unlike one of present embodiment and specific embodiment one to five：In step 5
Annealing temperature carries out homogenizing annealing 32h under conditions of being 470 DEG C.It is other identical with one of specific embodiment one to five.
Specific embodiment seven：Unlike one of present embodiment and specific embodiment one to six：It is squeezed in step 7
It is 390 DEG C to press temperature.It is other identical with one of specific embodiment one to six.
Specific embodiment eight：Unlike one of present embodiment and specific embodiment one to seven：In step 8
Temperature is dissolved under the conditions of being 470 DEG C.It is other identical with one of specific embodiment one to seven.
Specific embodiment nine：Unlike one of present embodiment and specific embodiment one to eight：It is controlled in step 9
Drawing deformation processed is 2.5%.It is other identical with one of specific embodiment one to eight.
Specific embodiment ten：Unlike one of present embodiment and specific embodiment one to nine：In step 10
It is 121 DEG C~124 DEG C that level-one timeliness, which is heated to temperature, keeps the temperature 4.5h, and it is 162 DEG C~168 DEG C that second level timeliness, which is heated to temperature,
Keep the temperature 12h.It is other identical with one of specific embodiment one to nine.
Beneficial effects of the present invention are verified using following embodiment：
Embodiment one：
A kind of manufacturing method of aviation alloyed aluminium section bar of the present embodiment is specifically prepared according to following steps：
First, melting：It is Zn by the mass percent of element：6.4%th, Mg：2.3%th, Cu：2.1%th, Zr：0.10%th, Si：
0.05%th, Fe：0.08%th, Mn：0.05%th, Cr：0.02%th, Ti：0.03% and surplus weigh fine aluminium ingot, fine copper ingot, pure for Al
Magnesium ingot, pure zinc ingot, aluminium zircaloy ingot, aluminum titanium alloy ingot and aluminium Ti, B grain graining agent are simultaneously added in dry smelting furnace,
Temperature is melting 7h under the conditions of 730 DEG C, obtains molten aluminium alloy；
2nd, it casts：By the aluminium alloy solution that step 1 obtains temperature be 720 DEG C, casting speed 85mm/min, cooling water it is strong
Spend for 0.02MPa, cooling water temperature be 19 DEG C under conditions of be cast as the casting rod of a diameter of 192mm；
3rd, it cuts off：The casting rod that step 2 obtains is cut into the stub that length is 450mm；
4th, railway carriage：The stub vehicle that step 3 obtains is gone to the oxide skin on surface, obtains aluminium alloy cast ingot；
5th, it anneals：Homogenizing annealing is carried out under conditions of being 470 DEG C in annealing temperature by the aluminium alloy cast ingot that step 4 obtains
32h；
6th, it heats：Aluminium alloy cast ingot after step 5 is annealed is put into resistance-heated furnace, and aluminium alloy cast ingot is heated to 410
DEG C, the aluminium alloy cast ingot that obtains that treated；
7th, it squeezes：Step 6 treated aluminium alloy cast ingot milling is squeezed by section mould for aluminium alloy, extrusion temperature 390
DEG C, obtain the aluminium alloy extrusions that length is 10000mm；
8th, it is dissolved water quenching：It is dissolved under the conditions of being 470 DEG C in temperature by the aluminium alloy extrusions that step 7 obtains, after keeping the temperature 1h
It comes out of the stove water quenching；
9th, it stretches：Step 8 is dissolved aluminium alloy extrusions tension straingtening in 4h after water quenching, control drawing deformation is
2.5%；
Tenth, timeliness：The aluminium alloy extrusions of step 9 tension straingtening is subjected to two-stage time effect, wherein, first order timeliness is heated to temperature
It is 120 DEG C to spend, and keeps the temperature 4h, it is 165 DEG C that second level timeliness, which is heated to temperature, keeps the temperature 12h, aviation alloyed aluminium type is prepared
Material.
Aviation alloyed aluminium section bar entity size manufactured in the present embodiment, surface quality are good, mouldability in industrial production
Can be good, comprehensive mechanical property is excellent, and T74511 state section bars tensile strength is not less than 540N/mm2, Proof strength of non-proportional
Not less than 480N/mm2, elongation after fracture be not less than 8%；Exfoliation Corrosion is not less than EB grades.Making aviation is suitble to be closed with aluminium
Metal type material.
Claims (10)
- A kind of 1. method using two-stage time effect manufacture aviation alloyed aluminium section bar, it is characterised in that be specifically according to following steps It prepares：First, melting：It is Zn by the mass percent of element：5.9%~6.9%, Mg：2.0%~2.7%, Cu：1.9%~ 2.5%th, Zr：0.08%~0.15%, Si：≤ 0.12%, Fe：≤ 0.15%, Mn：≤ 0.10%, Cr：≤ 0.04%, Ti：≤ 0.06% and surplus weigh fine aluminium ingot, fine copper ingot, pure magnesium ingot, pure zinc ingot, aluminium zircaloy ingot, aluminum titanium alloy ingot and aluminium titanium boron for Al Grain refiner is simultaneously added in dry smelting furnace, and melting 6h~7h under the conditions of being 720 DEG C~760 DEG C in temperature obtains aluminium Alloy molten solution；2nd, it casts：By the molten aluminium alloy that step 1 obtains temperature be 715 DEG C~750 DEG C, casting speed be 80mm/min~ 90 mm/min, cooling water intensity are the MPa of 0.01 MPa~0.03, cooling water temperature is cast as under conditions of being 18 DEG C~25 DEG C The casting rod of a diameter of 192mm~195mm；3rd, it cuts off：The casting rod that step 2 obtains is cut into the stub that length is 400mm~450mm；4th, railway carriage：The stub vehicle that step 3 obtains is gone to the oxide skin on surface, obtains aluminium alloy cast ingot；5th, it anneals：It is carried out under conditions of being 460 DEG C~475 DEG C in annealing temperature by the aluminium alloy cast ingot that step 4 obtains uniform Annealing 31h~33h；6th, it heats：Aluminium alloy cast ingot after step 5 is annealed is put into resistance-heated furnace, and aluminium alloy cast ingot is heated to 380 DEG C~410 DEG C, the aluminium alloy cast ingot that obtains that treated；7th, it squeezes：Step 6 treated aluminium alloy cast ingot is squeezed by section mould for aluminium alloy, extrusion temperature is 380 DEG C ~400 DEG C, obtain the aluminium alloy extrusions that length is 10000mm~10100mm；8th, it is dissolved water quenching：It is dissolved, protects under the conditions of being 465 DEG C~475 DEG C in temperature by the aluminium alloy extrusions that step 7 obtains It comes out of the stove after warm 1h~1.2h water quenching；9th, it stretches：Step 8 is dissolved aluminium alloy extrusions tension straingtening in 4h after water quenching, control drawing deformation is 1.5%~3.0%；Tenth, timeliness：The aluminium alloy extrusions of step 9 tension straingtening is subjected to two-stage time effect, wherein, first order timeliness is heated to temperature It is 120 DEG C~125 DEG C to spend, and keeps the temperature 4h~5h, and it is 160 DEG C~170 DEG C that second level timeliness, which is heated to temperature, keeps the temperature 11h~13h, Aviation alloyed aluminium section bar is prepared.
- 2. a kind of method using two-stage time effect manufacture aviation alloyed aluminium section bar according to claim 1, feature exist The mass percent that element is pressed in step 1 is Zn：6.2%~6.5%, Mg：2.2%~2.5%, Cu：2.0%~ 2.2%th, Zr：0.09%~0.12%, Si：≤ 0.10%, Fe：≤ 0.12%, Mn：≤ 0.06%, Cr：≤ 0.03%, Ti：≤ 0.05% and surplus weigh fine aluminium ingot, fine copper ingot, pure magnesium ingot, pure zinc ingot, aluminium zircaloy ingot, aluminum titanium alloy ingot and aluminium titanium boron for Al Grain refiner is simultaneously added in dry smelting furnace.
- 3. a kind of method using two-stage time effect manufacture aviation alloyed aluminium section bar according to claim 2, feature exist The mass percent that element is pressed in step 1 is Zn：6.4%th, Mg：2.3%th, Cu：2.1%th, Zr：0.10%th, Si：0.05%th, Fe：0.08%th, Mn：0.05%th, Cr：0.02%th, Ti：0.03% and surplus weigh fine aluminium ingot, fine copper ingot, pure magnesium ingot, pure for Al Zinc ingot metal, aluminium zircaloy ingot, aluminum titanium alloy ingot and aluminium Ti, B grain graining agent are simultaneously added in dry smelting furnace.
- 4. a kind of method using two-stage time effect manufacture aviation alloyed aluminium section bar according to claim 3, feature exist Melting under the conditions of being 730 DEG C in temperature in step 1.
- 5. a kind of method using two-stage time effect manufacture aviation alloyed aluminium section bar according to claim 4, feature exist Temperature is 720 DEG C, casting speed is 85 mm/min, cooling water intensity is 0.02 MPa, cooling water temperature is in step 2 It is cast under conditions of 19 DEG C.
- 6. a kind of method using two-stage time effect manufacture aviation alloyed aluminium section bar according to claim 5, feature exist Homogenizing annealing 32h is carried out under conditions of being 470 DEG C in annealing temperature in step 5.
- 7. a kind of method using two-stage time effect manufacture aviation alloyed aluminium section bar according to claim 6, feature exist Extrusion temperature is 390 DEG C in step 7.
- 8. a kind of method using two-stage time effect manufacture aviation alloyed aluminium section bar according to claim 7, feature exist It is dissolved under the conditions of being 470 DEG C in temperature in step 8.
- 9. a kind of method using two-stage time effect manufacture aviation alloyed aluminium section bar according to claim 8, feature exist It is 2.5% that drawing deformation is controlled in step 9.
- 10. a kind of method using two-stage time effect manufacture aviation alloyed aluminium section bar according to claim 9, feature exist It is 121 DEG C~124 DEG C that first order timeliness, which is heated to temperature, in step 10, keeps the temperature 4.5h, second level timeliness is heated to temperature and is 162 DEG C~168 DEG C, keep the temperature 12h.
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