CN104404415B - Preparation process of aviation aluminum alloy ingot and aluminum alloy ingot - Google Patents
Preparation process of aviation aluminum alloy ingot and aluminum alloy ingot Download PDFInfo
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- CN104404415B CN104404415B CN201410762704.2A CN201410762704A CN104404415B CN 104404415 B CN104404415 B CN 104404415B CN 201410762704 A CN201410762704 A CN 201410762704A CN 104404415 B CN104404415 B CN 104404415B
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- 229910000838 Al alloy Inorganic materials 0.000 title claims abstract description 127
- 238000002360 preparation method Methods 0.000 title claims abstract description 27
- 238000005266 casting Methods 0.000 claims abstract description 123
- 229910052782 aluminium Inorganic materials 0.000 claims abstract description 62
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims abstract description 62
- 238000007872 degassing Methods 0.000 claims abstract description 16
- 238000001914 filtration Methods 0.000 claims abstract description 8
- 238000002156 mixing Methods 0.000 claims abstract description 7
- 238000002844 melting Methods 0.000 claims description 54
- 230000008018 melting Effects 0.000 claims description 54
- 239000004411 aluminium Substances 0.000 claims description 48
- 238000000265 homogenisation Methods 0.000 claims description 27
- 238000005516 engineering process Methods 0.000 claims description 26
- 238000010438 heat treatment Methods 0.000 claims description 22
- 239000000498 cooling water Substances 0.000 claims description 18
- 239000000155 melt Substances 0.000 claims description 4
- 230000014759 maintenance of location Effects 0.000 claims description 3
- 238000001514 detection method Methods 0.000 abstract description 46
- 238000007670 refining Methods 0.000 abstract description 11
- 238000003723 Smelting Methods 0.000 abstract description 10
- 229910045601 alloy Inorganic materials 0.000 description 51
- 239000000956 alloy Substances 0.000 description 51
- 239000011777 magnesium Substances 0.000 description 48
- 239000010949 copper Substances 0.000 description 44
- 239000011701 zinc Substances 0.000 description 42
- 238000000034 method Methods 0.000 description 33
- 239000010936 titanium Substances 0.000 description 23
- 230000008569 process Effects 0.000 description 15
- 229910052749 magnesium Inorganic materials 0.000 description 14
- 229910052725 zinc Inorganic materials 0.000 description 14
- 229910052751 metal Inorganic materials 0.000 description 13
- 239000002184 metal Substances 0.000 description 13
- 239000000047 product Substances 0.000 description 13
- 238000012797 qualification Methods 0.000 description 13
- 239000000203 mixture Substances 0.000 description 12
- 239000002245 particle Substances 0.000 description 11
- 239000002994 raw material Substances 0.000 description 11
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 11
- XKRFYHLGVUSROY-UHFFFAOYSA-N Argon Chemical compound [Ar] XKRFYHLGVUSROY-UHFFFAOYSA-N 0.000 description 10
- HCHKCACWOHOZIP-UHFFFAOYSA-N Zinc Chemical compound [Zn] HCHKCACWOHOZIP-UHFFFAOYSA-N 0.000 description 10
- 238000009826 distribution Methods 0.000 description 10
- 229910052802 copper Inorganic materials 0.000 description 8
- 239000013078 crystal Substances 0.000 description 8
- 239000000843 powder Substances 0.000 description 8
- 239000002904 solvent Substances 0.000 description 8
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 description 7
- 230000004907 flux Effects 0.000 description 7
- 238000004519 manufacturing process Methods 0.000 description 7
- 239000000463 material Substances 0.000 description 7
- 238000001556 precipitation Methods 0.000 description 7
- 238000005070 sampling Methods 0.000 description 7
- 238000003756 stirring Methods 0.000 description 7
- 239000011651 chromium Substances 0.000 description 6
- 239000007788 liquid Substances 0.000 description 6
- 208000037656 Respiratory Sounds Diseases 0.000 description 5
- 238000005275 alloying Methods 0.000 description 5
- 238000004458 analytical method Methods 0.000 description 5
- 229910052786 argon Inorganic materials 0.000 description 5
- 239000000919 ceramic Substances 0.000 description 5
- 238000005260 corrosion Methods 0.000 description 5
- 230000000694 effects Effects 0.000 description 5
- 239000007789 gas Substances 0.000 description 5
- 239000011572 manganese Substances 0.000 description 5
- 238000012545 processing Methods 0.000 description 5
- 239000006104 solid solution Substances 0.000 description 5
- 229910052726 zirconium Inorganic materials 0.000 description 5
- 229910018575 Al—Ti Inorganic materials 0.000 description 4
- 229910018580 Al—Zr Inorganic materials 0.000 description 4
- 229910052804 chromium Inorganic materials 0.000 description 4
- 230000007797 corrosion Effects 0.000 description 4
- 238000009413 insulation Methods 0.000 description 4
- 239000011159 matrix material Substances 0.000 description 4
- 238000007254 oxidation reaction Methods 0.000 description 4
- 229910052710 silicon Inorganic materials 0.000 description 4
- 239000000126 substance Substances 0.000 description 4
- 229910018167 Al—Be Inorganic materials 0.000 description 3
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 description 3
- FYYHWMGAXLPEAU-UHFFFAOYSA-N Magnesium Chemical compound [Mg] FYYHWMGAXLPEAU-UHFFFAOYSA-N 0.000 description 3
- 238000001816 cooling Methods 0.000 description 3
- 238000001125 extrusion Methods 0.000 description 3
- 239000006052 feed supplement Substances 0.000 description 3
- 238000007689 inspection Methods 0.000 description 3
- 229910052742 iron Inorganic materials 0.000 description 3
- 229910052748 manganese Inorganic materials 0.000 description 3
- 230000003647 oxidation Effects 0.000 description 3
- 238000001953 recrystallisation Methods 0.000 description 3
- 230000001629 suppression Effects 0.000 description 3
- 238000012360 testing method Methods 0.000 description 3
- 229910052719 titanium Inorganic materials 0.000 description 3
- 229910018571 Al—Zn—Mg Inorganic materials 0.000 description 2
- 229910000967 As alloy Inorganic materials 0.000 description 2
- TWRXJAOTZQYOKJ-UHFFFAOYSA-L Magnesium chloride Chemical compound [Mg+2].[Cl-].[Cl-] TWRXJAOTZQYOKJ-UHFFFAOYSA-L 0.000 description 2
- 229910017708 MgZn2 Inorganic materials 0.000 description 2
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 description 2
- 229910000831 Steel Inorganic materials 0.000 description 2
- 238000000137 annealing Methods 0.000 description 2
- 150000001875 compounds Chemical class 0.000 description 2
- 239000000470 constituent Substances 0.000 description 2
- PCHJSUWPFVWCPO-UHFFFAOYSA-N gold Chemical compound [Au] PCHJSUWPFVWCPO-UHFFFAOYSA-N 0.000 description 2
- 229910052737 gold Inorganic materials 0.000 description 2
- 239000010931 gold Substances 0.000 description 2
- 239000012535 impurity Substances 0.000 description 2
- 229910000765 intermetallic Inorganic materials 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000005457 optimization Methods 0.000 description 2
- 230000008520 organization Effects 0.000 description 2
- 238000012805 post-processing Methods 0.000 description 2
- 238000007493 shaping process Methods 0.000 description 2
- 239000010959 steel Substances 0.000 description 2
- 239000002699 waste material Substances 0.000 description 2
- 229910018182 Al—Cu Inorganic materials 0.000 description 1
- VYZAMTAEIAYCRO-UHFFFAOYSA-N Chromium Chemical compound [Cr] VYZAMTAEIAYCRO-UHFFFAOYSA-N 0.000 description 1
- 229910000737 Duralumin Inorganic materials 0.000 description 1
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 description 1
- WHXSMMKQMYFTQS-UHFFFAOYSA-N Lithium Chemical compound [Li] WHXSMMKQMYFTQS-UHFFFAOYSA-N 0.000 description 1
- 229910019086 Mg-Cu Inorganic materials 0.000 description 1
- XUIMIQQOPSSXEZ-UHFFFAOYSA-N Silicon Chemical compound [Si] XUIMIQQOPSSXEZ-UHFFFAOYSA-N 0.000 description 1
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 1
- 230000002180 anti-stress Effects 0.000 description 1
- 229910052788 barium Inorganic materials 0.000 description 1
- DSAJWYNOEDNPEQ-UHFFFAOYSA-N barium atom Chemical compound [Ba] DSAJWYNOEDNPEQ-UHFFFAOYSA-N 0.000 description 1
- 229910001626 barium chloride Inorganic materials 0.000 description 1
- WDIHJSXYQDMJHN-UHFFFAOYSA-L barium chloride Chemical compound [Cl-].[Cl-].[Ba+2] WDIHJSXYQDMJHN-UHFFFAOYSA-L 0.000 description 1
- 238000007664 blowing Methods 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 239000003795 chemical substances by application Substances 0.000 description 1
- 238000004140 cleaning Methods 0.000 description 1
- 235000019628 coolness Nutrition 0.000 description 1
- 210000001787 dendrite Anatomy 0.000 description 1
- 238000009792 diffusion process Methods 0.000 description 1
- 238000010790 dilution Methods 0.000 description 1
- 239000012895 dilution Substances 0.000 description 1
- 239000006185 dispersion Substances 0.000 description 1
- 230000003628 erosive effect Effects 0.000 description 1
- 238000005242 forging Methods 0.000 description 1
- 238000007499 fusion processing Methods 0.000 description 1
- 239000001257 hydrogen Substances 0.000 description 1
- 229910052739 hydrogen Inorganic materials 0.000 description 1
- 239000004615 ingredient Substances 0.000 description 1
- 229910052744 lithium Inorganic materials 0.000 description 1
- 229910001629 magnesium chloride Inorganic materials 0.000 description 1
- WPBNNNQJVZRUHP-UHFFFAOYSA-L manganese(2+);methyl n-[[2-(methoxycarbonylcarbamothioylamino)phenyl]carbamothioyl]carbamate;n-[2-(sulfidocarbothioylamino)ethyl]carbamodithioate Chemical compound [Mn+2].[S-]C(=S)NCCNC([S-])=S.COC(=O)NC(=S)NC1=CC=CC=C1NC(=S)NC(=O)OC WPBNNNQJVZRUHP-UHFFFAOYSA-L 0.000 description 1
- 238000013507 mapping Methods 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 230000005012 migration Effects 0.000 description 1
- 238000013508 migration Methods 0.000 description 1
- 229910052759 nickel Inorganic materials 0.000 description 1
- 230000001737 promoting effect Effects 0.000 description 1
- 238000000746 purification Methods 0.000 description 1
- 230000003014 reinforcing effect Effects 0.000 description 1
- 238000007788 roughening Methods 0.000 description 1
- 238000005204 segregation Methods 0.000 description 1
- 239000010703 silicon Substances 0.000 description 1
- 238000009864 tensile test Methods 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
Classifications
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
- C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
- C22F1/04—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon
- C22F1/053—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
-
- 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
Landscapes
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Crystallography & Structural Chemistry (AREA)
- Manufacture And Refinement Of Metals (AREA)
Abstract
The invention provides a preparation process of an aviation aluminum alloy ingot. The preparation process of the aviation aluminum alloy ingot comprises the following steps: (A) mixing a Cu source, an Mg source, a Zn source, a Ti source, a Zr source and an Al source, then smelting to obtain a smelted product; (B) sequentially degassing, filtering and refining the smelted product obtained in the step (A) on line to obtain an on-line processed product; (C) casting the on-line processed product obtained in the step (B) to obtain an aviation aluminum alloy ingot blank, wherein the casting rate is 8-14mm/min; (D) carrying out homogenizing treatment on the aviation aluminum alloy ingot blank obtained in the step (C) to obtain the aviation aluminum alloy ingot. According to the preparation process, the proper casting rate is adopted; the flaw detection eligibility rate of the aluminum alloy can be increased; experimental results show that the flaw detection eligibility rate of aluminum alloy 7050 and aluminum alloy 7A85 prepared by the preparation process of the aviation aluminum reaches 97-99%.
Description
Technical field
The invention belongs to technical field of metal, more particularly, to a kind of preparation technology of aviation alloyed aluminium ingot casting and aluminum
Alloy cast ingot.
Background technology
Aluminium alloy is the alloy general name with aluminum as matrix element, and the main alloying element including has copper, silicon, magnesium, zinc, manganese,
Also include the alloying elements such as nickel, ferrum, titanium, chromium, lithium.The density of aluminium alloy is low, but intensity is higher, near or above high-quality steel,
Plasticity is good, can be processed into various section bars, has excellent electric conductivity, heat conductivity and corrosion stability, is in Aeronautics and Astronautics, automobile, machine
A most widely used class nonferrous materials in tool manufacture, ship and chemical industry, its usage amount is only second to steel.
Generally, aluminium alloy more than yield strength 500MPa is referred to as ultrahigh-strength aluminum alloy, and they are with AL-Zn-Mg-
Heat-treatable strengthened aluminium alloy (abbreviation 7xxx line aluminium alloy) based on Cu system and Al-Zn-Mg system, from the middle of last century with
Come, in order to improve the mechanical property of Al-Zn-Mg line aluminium alloy, and solve high zinc, the serious stress existing is rotten in high-magnesium aluminum alloy
Erosion problem, abroad adds the element such as Cu, Cr, Mn in such aluminium alloy, thereby produces a series of new A L-Zn-Mg-Cu
Extra super duralumin alloy.It is tough due to having high specific strength and hardness, good hot-workability, excellent welding performance, high fracture
Degree, and it is widely used in aerospace field the advantages of high anti-stress-corrosion ability, and become important in this field
One of material.
Wherein, the 7A85 aluminium alloy in 7xxx line aluminium alloy (the external trade mark is 7085) and 7050 aluminium alloys are aircraft industry
Ideal structural material, new 7A85 aluminium alloy is mainly used in the thick big important primary structure member of specification of airliner, such as wing
Spar, fuselage reinforcing frame, gear support beam etc.；7050 aluminium alloys are used for manufacturing the main bearing member of aircraft, such as fuselage frame
Frame, dividing plate, wing wallboard, spar, rib, gear support beam etc..
Production technology includes melting, online treatment and casting still, the system of existing 7A85 aluminium alloy and 7050 aluminium alloys
The ingot blank flaw detection qualification rate of standby technique productions is relatively low.
Content of the invention
It is an object of the invention to provide a kind of preparation technology of aviation alloyed aluminium ingot casting and aluminium alloy cast ingot, the present invention
The aluminium alloy cast ingot flaw detection qualification rate that the preparation technology of the aviation alloyed aluminium ingot casting providing obtains is higher.
The present invention provides a kind of preparation technology of aviation alloyed aluminium ingot casting, comprises the following steps：
A) carry out melting by after the mixing of Cu source, Mg source, Zn source, Ti source, Zr source and Al source, obtain melting thing；
B) by described step A) the melting thing that obtains carries out online degasification, on-line filtration and in line thinning successively, obtains
Line processes product；
C) by described step B) the online treatment product that obtains cast, and obtains aviation alloyed aluminium ingot blank, described casting
The speed made is 8～14mm/min；
D) by described step C) the aviation alloyed aluminium ingot casting that obtains carries out homogenization heat treatment, obtains aviation alloyed aluminium
Ingot casting；
Described aviation alloyed aluminium ingot casting includes 7050 aluminium alloy cast ingots and 7A85 aluminium alloy cast ingot.
Preferably, described step A) specifically include following steps：
Carry out melting after Cu source, Zn source, Ti source, Zr source and Al source are mixed, after melt all melts, add Mg source and
The Be of 0-0.0009%, carries out melting, obtains melting thing.
Preferably, the temperature of described melting is 800～1050 DEG C.
Preferably, the temperature of described online degasification is 715～725 DEG C；
The gas flow rate of described online degasification is 25～35L/min；
Described carried out using Al-5Ti-B silk in line thinning.
Preferably, the speed of described casting is 9～13mm/min.
Preferably, the temperature of described casting is 650～770 DEG C.
Preferably, in described casting, the flow of cooling water is 10～20m3/h.
Preferably, when the length of described casting is between 0mm～300mm, the flow of cooling water in described casting process
For 10～11m3/h；
As the length ＞ 300mm of described casting, by the flow of cooling water in described casting process with (1m3/h)/50mm
Speed increase, until the flow of described cooling water reaches 19～20m3/h.
Preferably, the holding temperature of described homogenization heat treatment is 460～470 DEG C；
The temperature retention time of described homogenization heat treatment is 30～35 hours.
The present invention provides the aluminium alloy casting that the specification that the preparation technology as described in technique scheme is obtained is Φ 850mm
Ingot.
The present invention provides a kind of preparation technology of aviation alloyed aluminium ingot casting, comprises the following steps：A) by Cu source, Mg source,
Carry out melting after Zn source, Ti source, Zr source and the mixing of Al source, obtain melting thing；B) by described step A) the melting thing that obtains is successively
Carry out online degasification, on-line filtration and in line thinning, obtain online treatment product；C) by described step B) online treatment that obtains
Product is cast, and obtains aviation alloyed aluminium ingot blank, the speed of described casting is 8～14mm/min；D) by described step C)
The aviation alloyed aluminium ingot casting obtaining carries out homogenization heat treatment, obtains aviation alloyed aluminium ingot casting；Described aviation alloyed aluminium
Ingot casting includes 7050 aluminium alloy cast ingots and 7A85 aluminium alloy cast ingot.The preparation technology that the present invention provides adopts suitable casting speed
Degree, the aluminum melt being prevented from when casting are revealed, and reduce the crackle tendency at ingot casting center and the drawing crack tendency on ingot casting surface, carry
The flaw detection qualification rate of high-aluminium alloy.Test result indicate that, 7050 aluminum that are obtained of preparation technology of the aviation aluminum that the present invention provides
The flaw detection qualification rate of alloy cast ingot and 7A85 aluminium alloy cast ingot is 97～99%.
Brief description
In order to be illustrated more clearly that the embodiment of the present invention or technical scheme of the prior art, below will be to embodiment or existing
Have technology description in required use accompanying drawing be briefly described it should be apparent that, drawings in the following description be only this
Inventive embodiment, for those of ordinary skill in the art, on the premise of not paying creative work, can also basis
The accompanying drawing providing obtains other accompanying drawings.
The top layer of the 7A85 aluminium alloy cast ingot gate part that Fig. 1 obtains for the embodiment of the present invention 1 50 × under high power detection
Figure；
The top layer of the 7A85 aluminium alloy cast ingot gate part that Fig. 2 obtains for the embodiment of the present invention 1 200 × under high power detection
Figure；
The 1/4 of the 7A85 aluminium alloy cast ingot gate part that Fig. 3 obtains for the embodiment of the present invention 1 is in 50 × under high power detection
Figure；
The 1/4 of the 7A85 aluminium alloy cast ingot gate part that Fig. 4 obtains for the embodiment of the present invention 1 is in 200 × under high power inspection
Mapping；
The center portion of the 7A85 aluminium alloy cast ingot gate part that Fig. 5 obtains for the embodiment of the present invention 1 50 × under high power detection
Figure；
The center portion of the 7A85 aluminium alloy cast ingot gate part that Fig. 6 obtains for the embodiment of the present invention 1 200 × under high power detection
Figure；
The 7A85 bottom of aluminum alloy ingot top layer that Fig. 7 obtains for the embodiment of the present invention 1 50 × under high power detection figure；
The 7A85 bottom of aluminum alloy ingot top layer that Fig. 8 obtains for the embodiment of the present invention 1 200 × under high power detection figure；
The 1/4 of the 7A85 bottom of aluminum alloy ingot that Fig. 9 obtains for the embodiment of the present invention 1 is in 50 × under high power detection
Figure；
The 7A85 bottom of aluminum alloy ingot 1/4 that Figure 10 obtains for the embodiment of the present invention 1 is in 200 × under high power detection
Figure；
The center portion of the 7A85 bottom of aluminum alloy ingot that Figure 11 obtains for the embodiment of the present invention 1 50 × under high power detection
Figure；
The center portion of the 7A85 bottom of aluminum alloy ingot that Figure 12 obtains for the embodiment of the present invention 1 200 × under high power detection
Figure.
Specific embodiment
The present invention provides a kind of preparation technology of aviation alloyed aluminium ingot casting, comprises the following steps：
A) carry out melting by after the mixing of Cu source, Mg source, Zn source, Ti source, Zr source and Al source, obtain melting thing；
B) by described step A) the melting thing that obtains carries out online degasification, on-line filtration and in line thinning successively, obtains
Line processes product；
C) by described step B) the online treatment product that obtains cast, and obtains aviation alloyed aluminium ingot blank, described casting
The speed made is 8～14mm/min；
D) by described step C) the aviation alloyed aluminium ingot blank that obtains carries out homogenization heat treatment, obtains aviation alloyed aluminium
Ingot casting；
Described aviation alloyed aluminium ingot casting includes 7050 aluminium alloy cast ingots and 7A85 aluminium alloy cast ingot.
7050 aluminium alloy cast ingots and the flaw detection qualification rate of 7A85 aluminium alloy cast ingot that the preparation technology that the present invention provides obtains
Higher, 97～99% can be reached.
The present invention carries out melting by after the mixing of Cu source, Mg source, Zn source, Ti source, Zr source and Al source, obtains melting thing；This
Bright carry out described melting preferably in smelting furnace, the present invention is first sprinkled into No. two solvents preferably before shove charge in described smelting furnace,
Cu source, Zn source, Ti source, Zr source and Al source are loaded in smelting furnace, carries out melting, after melt softens staying and puts down, into stove
It is sprinkled into No. two solvent powder, treat that above-mentioned furnace charge all melts, when melt temperature reaches 720～740 DEG C, the Mg source of addition and 0-
0.0009% Be, is covered using No. two solvent powder after adding, melting after stirring, is obtained melting thing.
In shove charge, should carry out by order from small to large in principle, first will fill cobbing, refill big block, simultaneously
Intermediate alloy high for fusing point is contained at the middle and upper levels, the metal of easy scaling loss is contained in middle level.
In the present invention, mass fraction in described raw material for the described Cu is 1.3～2.6%, preferably 1.5～2.3%；
Present invention preferably employs pure Cu plate carries out described melting for Cu source, mass fraction >=99.95% of Cu in described pure Cu plate.
In the present invention, mass fraction in raw material used for the described Zn be 5.7～8.0%, preferably 6.0～
7.5%, more preferably 6.5～7.0%；Present invention preferably employs pure zinc ingot carries out described melting for Zn source, in described pure zinc ingot
The mass fraction of Zn is preferably >=99.99%.
In the present invention, mass fraction in raw material used for the described Ti is 0～0.06%, preferably 0～0.03%；
Described Ti with crystal grain thinning and can prevent ingot casting crackle, present invention preferably employs Al-Ti intermediate alloy carries out described melting for Ti source
Refining, in described Al-Ti intermediate alloy, the mass fraction of Ti is preferably 3～5%, more preferably 4%.
In the present invention, mass fraction in raw material used for the described Zr be 0.08～0.15%, preferably 0.1～
0.13%；Present invention preferably employs Al-Zr intermediate alloy carries out described melting for Zr source, Zr in described Al-Zr intermediate alloy
Mass fraction is preferably 3～5%, more preferably 4%.
In the present invention, mass fraction in raw material used for the described Mg be 1.2～2.6%, preferably 1.5～
2.5%；Present invention preferably employs pure Mg ingot carries out described melting for Mg source, in described pure Mg ingot the mass fraction of Mg preferably >=
99.95%.
In the present invention, the mass fraction of described Be is 0-0.0009%
In the present invention, mass fraction in raw material used for the described Al and the mass fraction sum of other components are
100%, present invention preferably employs pure Al ingot carries out described melting for Al source, in described pure Al ingot, the mass fraction of Al preferably >=
99.7%.
In the present invention, described No. two solvent powder are commercially available prod, and more standard is calculated in mass percent：KCl:32-
40%, MgCl2:38-46%, BaCl2:5-8%, model is No. two, and the company of home sale barium fluxing agent powder is very many, greatly
Type aluminium manufacturer also self manufacture, such as southwestern aluminum, each usage amount is preferably the 0.5～2% of above-mentioned raw materials total amount, more preferably
1%.
In the present invention, described aviation alloyed aluminium ingot casting includes 7050 aluminium alloy cast ingots and 7A85 aluminium alloy cast ingot, no
Content with the chemical composition contained by the aluminium alloy of the trade mark and chemical composition is different, e.g., in terms of mass fraction, 7050
In aluminium alloy, including 2.3% Cu, 2.3% Mg, 6.2% Zn, 0.02% Ti, 0.12% Zr and surplus Al；?
In 7A85 aluminium alloy, including 1.7% Cu, 1.7% Mg, 7.6% Zn, 0.12% Zr and surplus Al.
In the present invention, in described fusion process, the fire box temperature of melting is preferably 800～1050 DEG C, and more preferably 900
～1000 DEG C, in described melting, the temperature of melt is preferably 600～770 DEG C, more preferably 650～750 DEG C；Described melting when
Between be preferably 20～60min, more preferably 30～50min.
After completing described melting, the melt that preferred pair of the present invention obtains is sampled, to be analyzed to bath composition,
Then corresponding composition adjustment is carried out according to the content requirement of above-mentioned each composition, the method for described adjustment is those skilled in the art
Known to method.Specifically, decide whether to water down or feed supplement according to censorship result, water down or feed supplement according to quantity as follows
Carry out：
If producing 7A85 aluminium alloy cast ingot length 4200mm, 1 casting 4 is it is considered to oxidization burning loss 5%, ingot casting specification Φ
650, this alloy density is 2800kg/m3, then calculate total inventory=π × 0.652/4 × 4.2 × 4 × (1+5%) ×
2800≈17400kg.
, if Cu element on-the-spot sample analysis value is 1.3%, 1.6% need to be mended taking Cu element as a example,
Then need to mend Al-Cu intermediate alloy weight=17400 × (the 1.6%-1.3%)/40% ≈ 130kg of content 40%；
If Cu element on-the-spot sample analysis value 2.1%, need to water down to 1.9%,
Then need AL99.70 ingot total amount=17400 × (the 2.1%-1.9%)/1.9% ≈ 180kg watering down.
Before noting feed supplement or watering down, melt temperature should be properly increased to more than 750 DEG C, and the metal of addition or centre
Alloy should be dried, and the accident such as prevents from blowing out.
Present invention melt preferably in the middle of fire door is sampled, and is covered using described No. two solvent powder after sampling
Lid.
After completing composition adjustment, present invention preferably employs refine pipe carries out argon refine in stove, the time of described refine is excellent
Elect 15～30min, more preferably 20min as, the temperature of described refine is preferably 730～750 DEG C, more preferably 740 DEG C；Described
During refine, the height of bubble is not to be exceeded 80mm.
After completing described refine, melt is preferably stood by the present invention, obtains melting thing, and the time of described standing is preferred
≥25min.
After obtaining melting thing, described melting thing is carried out online degasification, on-line filtration and in line thinning by the present invention successively, obtains
To online treatment product.The present invention adopts twin-stage to rotate degasification aluminum melt in-line purification technology, solves traditional Ф 850mm and justifies ingot casting
Hydrogen content is higher, a difficult problem that is restricting forging product following process quality in kind and performance boost.
In the present invention, described online degasification preferably employs birotor refinery by de-gassing device, the flow of described refine gas
It is preferably 25～35L/min, more preferably 30L/min；The temperature of described refine is preferably 715～725 DEG C, and more preferably 720
℃；The rotating speed of described rotor is preferably 290～310rpm, more preferably 295～305rpm.
In the present invention, described on-line filtration preferably employs single-stage 30ppi ceramic filter plate and is filtered；Described thin online
Change and preferably employ Al-5Ti-B silk.
After completing online treatment, the online treatment obtaining product is cast by the present invention, obtains aviation alloyed aluminium ingot
Base, in the present invention, the speed of described casting is 8～14mm/min, preferably 9～13mm/min, more preferably 10～12mm/
min；The temperature of described casting is preferably 650～770 DEG C；In described casting process, the flow of cooling water is preferably 10～20m3/
h.In the present invention, at first, described casting speed is preferably 8～9mm/min, more preferably 8mm/min for described casting,
Described cooling water flow is preferably 10～11m3/ h, more preferably 10m3/h；After casting length reaches 300mm, by described casting
Speed is increased with the speed of (1mm/min)/50mm, until described casting speed reaches 13～14mm/min, more preferably 14mm/
min；The flow of described cooling water is with (1m3/ h) (after the length casting reaches 300mm, casting length often increases/50mm
50mm, discharge increases 1m3/ h) speed increase, until the flow of described cooling water reaches 19～20m3/h.Cooling water flow
Too high or too low, casting speed all can make to produce aluminum melt leakage during casting excessively slowly, causes casting process cannot be carried out；Casting speed
Spend and make the tendency increase of ingot casting centre burst, ingot casting surface produce drawing crack tendency increase soon, when serious, even generation aluminum melt draws
Leakage phenomenon.The present invention is cast using suitable casting speed, and to reduce centre burst tendency, ingot casting is also not in serious
Cold shut produces transversal crack., using the water-cooling method gradually strengthened, due to one time, water-cooled is weaker, and liquid cave is shallower, does not allow for the present invention
It is also easy to produce centre burst ingot casting, secondary water-cooled is relatively strengthened, rate of cooling greatly improves so that inside the aluminium alloy cast ingot that obtains
Dense structure, improves ingot casting shaping rate and internal metallurgical quality.
The present invention preferably cuts off the water when gate part liquid still has 1/3, stops when gate part horse back will depart from crystallizer, complete
Become described casting.
If using when prior art cast 7A85,7050 alloys big specification billet without fine aluminium shop fixtures technique, ingot casting bottom
It is also easy to produce crackle, or even whole entire crack.The present invention, using paving false bottom foundry engieering, without fine aluminium shop fixtures, exempts from wiper and scrapes water to return
Fire, is conducive to simplifying casting process, reduces production cost.
After completing described casting, the ingot casting that preferred pair of the present invention obtains is annealed, to go de-stress, the temperature of described annealing
Degree is preferably 350～450 DEG C, more preferably 380～420 DEG C；Preferably 6～10 hours time of described annealing, more preferably 7
～9 hours.
After obtaining aviation alloyed aluminium ingot blank, the present invention carries out the aviation alloyed aluminium obtaining ingot blank at homogenization heat
Reason, obtains aviation alloyed aluminium ingot casting, 7A85,7050 alloys mainly dissolve in matrix, shape by intensified element Zn, Mg, Cu solid solution
Become supersaturated solid solution, the precipitation strength phase of diffusion-precipitation distribution during timeliness and obtain superior performance, and more residual is not molten
The raising of performance will be unfavorable for.Meanwhile, big specification, high-alloying ingot casting also make alloying component segregation serious, therefore to casting
The homogenization heat treatment that ingot is carried out is quite important.
In the present invention, the Al separating out in Homogenization Process3Zr particle has a major impact to the overall performance of alloy, disperse
The Al of tiny distribution3Zr particle effectively can suppress crystal boundary migration, retains more Deformation structures in alloy after promoting solid solution, improves
Alloy mechanical property and anti-stress corrosion performance.Crystal boundary Al nearby3The microscopic appearance of Zr particle is observed and is shown, introduces slow rate liter
Warm process is to Al3Zr particle dispersion separates out has important function.Under normal circumstances, the Al in Homogenization Process3Zr particle separates out
Precipitation precipitation process, not only relevant with system free energy difference, also it is associated with the distribution of Zr element.During alloy graining, ingot casting
Middle Zr atom is enriched with dendrite center and dilution is although can be from transgranular to crystalline substance in Homogenization Process Zr atom near dendrite has a common boundary
Boundary spreads, but the precipitation peak value of Al3Zr particle is in high-temperature area, using single-stage or be rapidly heated Homogenization Treatment when, Zr
Atom often has little time diffusion just as Al3Zr particle separates out grows up.The Homogenization Treatment of therefore rapid heating condition, Al3Zr
Particle distribution density has substantially from the transgranular trend being gradually reduced to crystal boundary, and exists near crystal boundary and large range of no separate out
Area.
In the present invention, it should be ensured that stove before described aviation alloyed aluminium ingot casting shove charge is carried out homogenization heat treatment
Temperature≤350 DEG C, the present invention is preferably heated with 490～500 DEG C of heating-up temperature, until in-furnace temperature reaches 460～470 DEG C
When enter holding stage, the temperature of described insulation is preferably 460～470 DEG C, more preferably 465 DEG C；Described temperature retention time is 30
～35 hours, more preferably 32 hours.
In order to improve the combination property of aviation alloyed aluminium following process material, high-power blower can be adopted cold when coming out of the stove
But to less than 200 DEG C air coolings again, this kind of operation can slow down the roughening containing Zr particle to ingot casting, improves the effect of its suppression recrystallization.
After completing homogenization heat treatment, after aluminium alloy cast ingot that homogenization described in preferred pair of the present invention is thermally treated resulting in is carried out
Process, described post processing includes ingot casting sawing, processing and detection, at described post processing can need according to actual production
Reason, the present invention does not do special restriction.
Present invention also offers a kind of specification is the aluminium alloy cast ingot of Φ 850mm, according to the system described in technique scheme
Standby technique prepares, and flaw detection qualification rate is higher.The aluminium alloy cast ingot that the present invention provides includes 7050 aluminium alloy cast ingots and 7A85
Aluminium alloy cast ingot.
In the present invention, described 7050 aluminium alloy cast ingots preferably include the component of following mass fraction：Cu：2.0～
2.6%；Mg：1.9～2.6%；Zn：5.7～6.7%；Ti：0～0.06%；Zr：0.08～0.15%；Balance of Al；Described
The mass ratio of Zn and Mg is (2.5～3.0)：1.
The present invention is by the optimization of Cu content and Zn/Mg ratio and precise control, improve the intensity of 7050 aluminium alloys.
7050 aluminium alloys that the present invention provides include Cu, and the mass fraction of described Cu is 2.0～2.6%, preferably 2.1～
2.3%, more preferably 2.2%；Present invention preferably employs pure Cu plate carries out described melting, the mass fraction of Cu in described pure Cu plate
>=99.95%.
7050 aluminium alloys that the present invention provides include Mg, and the mass fraction of described Mg is 1.9～2.6%, preferably 2.1～
2.4%, more preferably 2.3%.Present invention preferably employs pure Mg ingot carries out described melting, the mass fraction of Mg in described pure Mg ingot
Preferably >=99.95%.
7050 aluminium alloys that the present invention provides include Zn, and the mass fraction of described Zn is 5.7～6.7%, preferably 6.0～
6.5%, more preferably 6.2%.In the present invention, the mass ratio of described Zn and Mg is (2.5～3.0)：1, preferably 2.7:1.
The present invention by the precise control of the mass ratio to Zn/Mg, make 7050 aluminium alloys that the present invention obtains have preferable intensity and
Toughness.Present invention preferably employs pure zinc ingot carries out described melting, in described pure zinc ingot, the mass fraction of Zn is preferably >=99.99%.
7050 aluminium alloys that the present invention provides include Ti, and described Ti with crystal grain thinning and can prevent ingot casting crackle.At this
In bright, the mass fraction of described Ti is 0～0.06%, preferably 0.01～0.03%, more preferably 0.02%.The present invention is preferred
Described melting is carried out using Al-Ti intermediate alloy, in described Al-Ti intermediate alloy, the mass fraction of Ti is preferably 3～5%, more
It is preferably 4%.
7050 aluminium alloys that the present invention provides include Zr, and the mass fraction of described Zr is preferably 0.08～0.15%, preferably
For 0.10～0.13%, more preferably 0.12%.Present invention preferably employs Al-Zr intermediate alloy carries out described melting, described Al-
In Zr intermediate alloy, the mass fraction of Zr is preferably 3～5%, more preferably 4%.Zr as the important addition element in alloy,
Compound Al between in the material mainly with the granulated metal of small and dispersed distribution3Zr form exists.This intermetallic compound possesses
Two kinds of forms：A kind of is the Al directly separating out from melt3Zr primary phase, has the effect of refinement as-cast grain；Another kind is
The granular Al of the small and dispersed distribution that during subsequent thermal processing, (as ingot homogenization) is decomposed to form3Zr secondary phase, strong suppression
Recrystallization tendency during subsequent thermal processing processed, and as the original position particle in ag(e)ing process to the precipitation distribution of η phase, state
Play an important role.
In the present invention, mass fraction in raw material used for the described Al and the mass fraction sum of other components are
100%, present invention preferably employs pure Al ingot carries out described melting, in described pure Al ingot, the mass fraction of Al is preferably >=99.7%.
In the present invention, described 7050 aluminium alloys are the aluminium alloy of Φ 850mm for specification.
In the present invention, some impurity are also included in described 7050 aluminium alloys, e.g., one of Si, Fe, Mn and Cr or several
Kind, mass fraction≤0.12% of described Si；Mass fraction≤0.15% of described Fe；The mass fraction of described Mn≤
0.10%；Mass fraction≤0.04% of described Cr.
In 7050 aluminium alloys that the present invention provides, Zn, Mg, Cu are main alloy elements, and Zn, Mg element is as alloy
Main intensified element, mainly in the alloy with solid solution, balance phase η (MgZn2)、T(Al2Mg3Zn3) and non-equilibrium phase η '
Form exists, and also there is a certain amount of AlCuFe, S (AlCuMg) phase in addition in alloy.η ' the phase separating out in ag(e)ing process, is to close
The main hardening constituent of gold.Cu is mainly dissolved in matrix, plays assisted and strengthened effect, can also reduce transgranular current potential and crystal boundary between
Differ from and improve stress corrosion performance.
The aviation alloyed aluminium ingot casting that the present invention provides includes 7A85 aluminium alloy, and described 7A85 aluminium alloy preferably includes following
The component of mass fraction：
Cu：1.3～2.0%；Mg：1.2～1.8%；Zn：7.0～8.0%；Zr：0.08～0.15%；Balance of Al；Institute
The mass ratio stating Zn and Mg is (4.5～5.0)：1.
The present invention is by the optimization of Cu content and Zn/Mg ratio and precise control, improve the intensity of 7A85 aluminium alloy.
The 7A85 aluminium alloy that the present invention provides includes Cu, and the mass fraction of described Cu is 1.3～2.0%, preferably 1.5～
1.8%, more preferably 1.7%；Present invention preferably employs pure Cu plate carries out described melting, the mass fraction of Cu in described pure Cu plate
>=99.95%.
The 7A85 aluminium alloy that the present invention provides includes Mg, and the mass fraction of described Mg is 1.2～1.8%, preferably 1.5～
1.7%, more preferably 1.6～1.7%.Present invention preferably employs pure Mg ingot carries out described melting, the matter of Mg in described pure Mg ingot
Amount fraction is preferably >=99.95%.
The 7A85 aluminium alloy that the present invention provides includes Zn, and the mass fraction of described Zn is 7.0～8.0%, preferably 7.2～
7.8%, more preferably 7.6%.In the present invention, the mass ratio of described Zn and Mg is (4.5～5.0)：1, preferably 4.8:1.
The present invention by the precise control of the mass ratio to Zn/Mg, make the 7A85 aluminium alloy that the present invention obtains have preferable intensity and
Toughness.Present invention preferably employs pure zinc ingot carries out described melting, in described pure zinc ingot, the mass fraction of Zn is preferably >=99.99%.
The 7A85 aluminium alloy that the present invention provides includes Zr, and the mass fraction of described Zr is preferably 0.08～0.15%, preferably
For 0.10～0.13%, more preferably 0.12%.Present invention preferably employs Al-Zr intermediate alloy carries out described melting, described Al-
In Zr intermediate alloy, the mass fraction of Zr is preferably 3～5%, more preferably 4%.Zr as the important addition element in alloy,
Compound Al between in the material mainly with the granulated metal of small and dispersed distribution3Zr form exists.This intermetallic compound possesses
Two kinds of forms：A kind of is the Al directly separating out from melt3Zr primary phase, has the effect of refinement as-cast grain；Another kind is
The granular Al of the small and dispersed distribution that during subsequent thermal processing, (as ingot homogenization) is decomposed to form3Zr secondary phase, strong suppression
Recrystallization tendency during subsequent thermal processing processed, and as the original position particle in ag(e)ing process to the precipitation distribution of η phase, state
Play an important role.
In the present invention, mass fraction in raw material used for the described Al and the mass fraction sum of other components are
100%, present invention preferably employs pure Al ingot carries out described melting, in described pure Al ingot, the mass fraction of Al is preferably >=99.7%.
In the present invention, described 7A85 aluminium alloy is the aluminium alloy of Φ 850mm for specification.
In the present invention, some impurity, e.g., one of Si, Fe, Mn, Ti and Cr are also included in described 7A85 aluminium alloy
Or several, mass fraction≤0.06% of described Si；Mass fraction≤0.08% of described Fe；The mass fraction of described Mn≤
0.04%；Mass fraction≤0.04% of described Cr；Mass fraction≤0.06% of Ti.
In the 7A85 aluminium alloy that the present invention provides, Zn, Mg, Cu are main alloy elements, and Zn, Mg element is as alloy
Main intensified element, mainly in the alloy with solid solution, balance phase η (MgZn2)、T(Al2Mg3Zn3) and non-equilibrium phase η '
Form exists, and also there is a certain amount of AlCuFe, S (AlCuMg) phase in addition in alloy.η ' the phase separating out in ag(e)ing process, is to close
The main hardening constituent of gold.Cu is mainly dissolved in matrix, plays assisted and strengthened effect, can also reduce transgranular current potential and crystal boundary between
Differ from and improve stress corrosion performance.
The present invention deforms what Al alloys andMg alloys product supersonic testing method obtained to the present invention according to GB/T 6519-2013
Aviation alloyed aluminium has carried out carrying out flaw detection, and result shows, the flaw detection qualification rate of the aviation alloyed aluminium that the present invention provides is 97
～99%.
The present invention is according to GB/T228《Metal material tensile testing at ambient temperature》The aviation alloyed aluminium that the present invention is obtained
Carry out intensity detection, result shows, the intensity of the aviation alloyed aluminium that the present invention provides is 520MPa.
The present invention deforms aluminum and the Al-alloy products microscopic structure method of inspection to the present invention according to GB/T 3246.1-2000
The aviation alloyed aluminium obtaining has carried out high power detection.
The present invention provides a kind of preparation technology of aviation alloyed aluminium ingot casting, comprises the following steps：A) by Cu source, Mg source,
Carry out melting after Zn source, Ti source, Zr source and the mixing of Al source, obtain melting thing；B) by described step A) the melting thing that obtains is successively
Carry out online degasification, on-line filtration and in line thinning, obtain online treatment product；C) by described step B) online treatment that obtains
Product is cast, and obtains aviation alloyed aluminium ingot blank, the speed of described casting is 8～14mm/min；D) by described step C)
The aviation alloyed aluminium ingot casting obtaining carries out homogenization heat treatment, obtains aviation alloyed aluminium ingot casting；Described aviation alloyed aluminium
Ingot casting includes 7050 aluminium alloy cast ingots and 7A85 aluminium alloy cast ingot.The preparation technology that the present invention provides adopts suitable casting speed
Degree, the aluminum melt being prevented from when casting are revealed, and reduce the crackle tendency at ingot casting center and the drawing crack tendency on ingot casting surface, carry
The flaw detection qualification rate of high-aluminium alloy.Test result indicate that, 7050 aluminum that are obtained of preparation technology of the aviation aluminum that the present invention provides
The flaw detection qualification rate of alloy and 7A85 aluminium alloy is 97～99%.
In order to further illustrate the present invention, a kind of aviation alloyed aluminium ingot casting to present invention offer with reference to embodiments
Preparation technology and its aluminium alloy cast ingot be described in detail, but limiting the scope of the present invention can not be understood as.
In the examples below, raw material used meet claimed below：
Remelted aluminum ingot：Al >=99.7%；Remelting magnesium ingot：Mg >=99.95%；Cathode copper：Cu >=99.95%；Zinc ingot metal：Zn≥
99.99%；Intermediate alloy：Al-15Mn, Al-4Cr, Al-4Ti, Al-4Zr, Al-3Be：In above-mentioned all intermediate alloys, Fe, Si
≤ 0.6%, other≤0.1%.Al-10Fe：Si≤0.6%, other≤0.1%.In line thinning：Al-5Ti-B Φ 9.5mm silk.
Auxiliary material used meets claimed below：
Liquid argon：Purity >=99.98%, H2O≤10ppm, [H2]≤5ppm, [O2]≤10ppm；2# flux：Technical grade；?
Line filters：30ppi ceramic filter plate.
During alloying ingredient should reasonably combined using low ferrum sial ingot with one-level waste material itself, high-precision aluminium ingot consumption >=50%,
One-level waste material consumption requires≤30%, requires raw material surface cleaning clean, copper, magnesium, zinc element are directly with simple metal during dispensing
Dispensing, other are with intermediate alloy dispensing.
Embodiment 1
Produce extrusion ingot length 4200mm, ingot casting specification is the 7A85 aluminium alloy of Φ 850.1 casting 4 is it is considered to oxidation is burnt
Damage 5%, this alloy density is 2800kg/m3, then calculate total inventory=π × 0.852/ 4 × 4.2 × 4 × (1+5%) ×
2800≈28400kg.
Uniformly be sprinkled into the 2# solvent powder of 65kg in smelting furnace, then by pure for 482kg Cu plate, 2156kg pure Zn ingot,
142kgAl-Ti intermediate alloy, 851kgAl-Zr intermediate alloy and 24287kgAL ingot carry out shove charge by order from small to large, that is,
First filled cobbing, refilled big block, intermediate alloy high for fusing point is contained at the middle and upper levels simultaneously, during the metal of easy scaling loss is contained in
Layer.The fire box temperature of smelting furnace controls at≤1050 DEG C, and melt temperature controls at≤770 DEG C, when melt softening stays and changes flat
Afterwards, uniformly it is sprinkled into the 2# ground flux of 130kg into stove, and stir metal in good time.
After furnace charge has all melted, melt temperature reaches the Al-Be adding 482kg Mg ingot and 8.5kg when 730 DEG C about
Intermediate alloy.Adition process and being covered with 89kg2# ground flux after adding, usage amount is defined by covering all.Should enter after adding
Row thoroughly stirs, and by stable for temperature adjustment at 740 DEG C about, carries out stokehold sampling after about spending 20 minutes.
Sampling must be carried out in melt in the middle of fire door, according to the control in both analysis result and technique scheme
Requirement carries out composition adjustment.
After the completion of composition adjustment, argon refine in stove, refining time 20 minutes, refining temperature 740 are carried out using refine pipe
DEG C about, during refine, bubble is highly not to be exceeded 80mm.
Should be stood after the completion of refine, time of repose at least 25 minutes.
Melt after standing is carried out online degasification using birotor refinery by de-gassing device, refine gas consumption is 30L/min,
Refining temperature is 720 ± 5 DEG C, and rotor speed is 300 ± 5rpm；Then mistake online is carried out using single-stage 30ppi ceramic filter plate
Filter, changes and requires during screen plate to check the integrity of screen plate, and ensure to be installed in place, carefully put mass, and fitted
Work as baking；Then according to the amount of 1.5kg/t adds Al-5Ti-B silk, carry out in line thinning.
After completing online treatment, melt is cast, casting temperature is 735 DEG C, when casting starts, cast vehicle speed
For 8mm/min, cooling water flow is 10m3/ h, after length to be cast reaches 300mm, by casting speed with (1mm/min)/
The increasing amount adjustment of 50mm to 14mm/min, by cooling water flow with (1m3/ h)/50mm increasing amount adjustment to 20m3/h.
Cut off the water when gate part liquid still has 1/3 during casting ending, stop when gate part horse back will depart from crystallizer, sternly
Prohibit water droplet to gate part.
After the completion of casting, the ingot blank that casting is obtained carries out homogenization heat treatment, with 495 DEG C of heating-up temperature heating, plus
Heat enters insulation to after 465 DEG C, is incubated 32 hours, completes homogenization heat treatment.
Then anneal 8 hours at 360 DEG C, then sawing, sawing gate part and bottom are carried out accordingly to ingot casting
All about 350mm, obtain 7A85 aluminium alloy.Casting rate is 93%.
The present invention carries out carrying out flaw detection according to the 7A85 aluminium alloy that technique scheme obtains to the present invention, and result shows,
The flaw detection qualification rate of the 7A85 aluminium alloy that the present embodiment obtains is 99%.
The gate part of the 7A85 aluminium alloy that the present invention obtains to the present embodiment according to technique scheme has carried out high power inspection
Survey, result as shown in figs. 1 to 6, the top layer of the 7A85 aluminium alloy cast ingot gate part that Fig. 1 obtains for the embodiment of the present invention 1 50 ×
Under high power detection figure；The top layer of the 7A85 aluminium alloy cast ingot gate part that Fig. 2 obtains for the embodiment of the present invention 1 200 × under
High power detection figure；The 1/4 of the 7A85 aluminium alloy cast ingot gate part that Fig. 3 obtains for the embodiment of the present invention 1 is in 50 × under high power
Detection figure；The 1/4 of the 7A85 aluminium alloy cast ingot gate part that Fig. 4 obtains for the embodiment of the present invention 1 is in 200 × under high power detection
Figure；The center portion of the 7A85 aluminium alloy cast ingot gate part that Fig. 5 obtains for the embodiment of the present invention 1 50 × under high power detection figure；Fig. 6
The center portion of the 7A85 aluminium alloy cast ingot gate part obtaining for the embodiment of the present invention 1 200 × under high power detection figure.By Fig. 1～6
As can be seen that the 7A85 aluminum alloy organization that the present embodiment obtains is fine and close, uniformity is preferable.
The bottom of the 7A85 aluminium alloy that the present invention obtains to the present embodiment according to technique scheme has carried out high power detection,
Result as shown in Fig. 7～12,7A85 bottom of aluminum alloy ingot top layer that Fig. 7 obtains for the embodiment of the present invention 1 50 × under height
Detection figure again；The 7A85 bottom of aluminum alloy ingot top layer that Fig. 8 obtains for the embodiment of the present invention 1 200 × under high power detection figure；
The 1/4 of the 7A85 bottom of aluminum alloy ingot that Fig. 9 obtains for the embodiment of the present invention 1 is in 50 × under high power detection figure；Figure 10 is
The 7A85 bottom of aluminum alloy ingot 1/4 that the embodiment of the present invention 1 obtains is in 200 × under high power detection figure；Figure 11 is the present invention
The center portion of the 7A85 bottom of aluminum alloy ingot that embodiment 1 obtains 50 × under high power detection figure；Figure 12 is the embodiment of the present invention 1
The center portion of the 7A85 bottom of aluminum alloy ingot obtaining 200 × under high power detection figure.Can be seen that this enforcement by Fig. 7～12
The 7A85 aluminum alloy organization that example obtains is fine and close, and uniformity is preferable.
Embodiment 2
Produce extrusion ingot length 4200mm, ingot casting specification is the 7A85 aluminium alloy of Φ 850.1 casting 4 is it is considered to oxidation is burnt
Damage 5%, this alloy density is 2800kg/m3, then calculate total inventory=π × 0.852/ 4 × 4.2 × 4 × (1+5%) ×
2800≈28400kg.
Uniformly be sprinkled into the 2# solvent powder of 65kg in smelting furnace, then by pure for 460kg Cu plate, 2059kg pure Zn ingot,
135kgAl-Ti intermediate alloy, 812kgAl-Zr intermediate alloy and 24474kgAL ingot carry out shove charge by order from small to large, that is,
First filled cobbing, refilled big block, intermediate alloy high for fusing point is contained at the middle and upper levels simultaneously, during the metal of easy scaling loss is contained in
Layer.The fire box temperature of smelting furnace controls at≤1050 DEG C, and melt temperature controls at≤770 DEG C, when melt softening stays and changes flat
Afterwards, uniformly it is sprinkled into the 2# ground flux of 130kg into stove, and stir metal in good time.
After furnace charge has all melted, melt temperature reaches the Al-Be adding 460kg Mg ingot and 8.5kg when 730 DEG C about
Intermediate alloy.Adition process and being covered with 89kg2# ground flux after adding, usage amount is defined by covering all.Should enter after adding
Row thoroughly stirs, and by stable for temperature adjustment at 740 DEG C about, carries out stokehold sampling after about spending 20 minutes.
Sampling must be carried out in melt in the middle of fire door, according to the control in both analysis result and technique scheme
Requirement carries out composition adjustment.
After the completion of composition adjustment, argon refine in stove, refining time 20 minutes, refining temperature 740 are carried out using refine pipe
DEG C about, during refine, bubble is highly not to be exceeded 80mm.
Should be stood after the completion of refine, time of repose at least 25 minutes.
Melt after standing is carried out online degasification using birotor refinery by de-gassing device, refine gas consumption is 30L/min,
Refining temperature is 720 ± 5 DEG C, and rotor speed is 300 ± 5rpm；Then mistake online is carried out using single-stage 30ppi ceramic filter plate
Filter, changes and requires during screen plate to check the integrity of screen plate, and ensure to be installed in place, carefully put mass, and fitted
Work as baking；Then according to the amount of 1.5kg/t adds Al-5Ti-B silk, carry out in line thinning.
After completing online treatment, melt is cast, casting temperature is 735 DEG C, when casting starts, cast vehicle speed
For 8mm/min, cooling water flow is 10m3/ h, after length to be cast reaches 300mm, by casting speed with (1mm/min)/
The increasing amount adjustment of 50mm to 14mm/min, by cooling water flow with (1m3/ h)/50mm increasing amount adjustment to 20m3/h.
Cut off the water when gate part liquid still has 1/3 during casting ending, stop when gate part horse back will depart from crystallizer, sternly
Prohibit water droplet to gate part.
After the completion of casting, the ingot blank that casting is obtained carries out homogenization heat treatment, with 495 DEG C of heating-up temperature heating, plus
Heat enters insulation to after 465 DEG C, is incubated 32 hours, completes homogenization heat treatment.
Then anneal 8 hours at 360 DEG C, then sawing, sawing gate part and bottom are carried out accordingly to ingot casting
All about 350mm, obtain 7A85 aluminium alloy.Casting rate is 92%.
The present invention carries out carrying out flaw detection according to the 7A85 aluminium alloy that technique scheme obtains to the present invention, and result shows,
The flaw detection qualification rate of the 7A85 aluminium alloy that the present embodiment obtains is 99%.
Embodiment 3
Produce extrusion ingot length 4000mm, ingot casting specification is 7050 aluminium alloys of Φ 850.1 casting 4 is it is considered to oxidation is burnt
Damage 5%, this alloy density is 2800kg/m3, then calculate total inventory=π × 0.852/ 4 × 4.0 × 4 × (1+5%) ×
2800≈26700kg.
Uniformly be sprinkled into the 2# solvent powder of 40kg in smelting furnace, then by pure for 614kg Cu plate, 1654kg pure Zn ingot,
133kgAl-Ti intermediate alloy, 800kgAl-Zr intermediate alloy and 22855kgAL ingot carry out shove charge by order from small to large, that is,
First filled cobbing, refilled big block, intermediate alloy high for fusing point is contained at the middle and upper levels simultaneously, during the metal of easy scaling loss is contained in
Layer.The fire box temperature of smelting furnace controls at≤1050 DEG C, and melt temperature controls at≤770 DEG C, when melt softening stays and changes flat
Afterwards, uniformly it is sprinkled into the 2# ground flux of 80kg into stove, and stir metal in good time.
After furnace charge has all melted, melt temperature reaches the Al-Be adding 614kg Mg ingot and 8.5kg when 730 DEG C about
Intermediate alloy.Adition process and being covered with 54kg2# ground flux after adding, usage amount is defined by covering all.Should enter after adding
Row thoroughly stirs, and by stable for temperature adjustment at 740 DEG C about, carries out stokehold sampling after about spending 20 minutes.
Sampling must be carried out in melt in the middle of fire door, according to the control in both analysis result and technique scheme
Requirement carries out composition adjustment.
After the completion of composition adjustment, argon refine in stove, refining time 20 minutes, refining temperature 740 are carried out using refine pipe
DEG C about, during refine, bubble is highly not to be exceeded 80mm.
Should be stood after the completion of refine, time of repose at least 25 minutes.
Melt after standing is carried out online degasification using birotor refinery by de-gassing device, refine gas consumption is 30L/min,
Refining temperature is 720 ± 5 DEG C, and rotor speed is 300 ± 5rpm；Then mistake online is carried out using single-stage 30ppi ceramic filter plate
Filter, changes and requires during screen plate to check the integrity of screen plate, and ensure to be installed in place, carefully put mass, and fitted
Work as baking；Then according to the amount of 1.5kg/t adds Al-5Ti-B silk, carry out in line thinning.
After completing online treatment, melt is cast, casting temperature is 735 DEG C, when casting starts, cast vehicle speed
For 8mm/min, cooling water flow is 10m3/ h, after length to be cast reaches 300mm, by casting speed with (1mm/min)/
The increasing amount adjustment of 50mm to 14mm/min, by cooling water flow with (1m3/ h)/50mm increasing amount adjustment to 20m3/h.
Cut off the water when gate part liquid still has 1/3 during casting ending, stop when gate part horse back will depart from crystallizer, sternly
Prohibit water droplet to gate part.
After the completion of casting, the ingot blank that casting is obtained carries out homogenization heat treatment, with 495 DEG C of heating-up temperature heating, plus
Heat enters insulation to after 465 DEG C, is incubated 32 hours, completes homogenization heat treatment.
Then anneal 8 hours at 360 DEG C, then sawing, sawing gate part and bottom are carried out accordingly to ingot casting
All about 350mm, obtain 7050 aluminium alloys.Casting rate is 90%.
The present invention carries out carrying out flaw detection according to 7050 aluminium alloys that technique scheme obtains to the present invention, and result shows,
The flaw detection qualification rate of 7050 aluminium alloys that the present embodiment obtains is 99%.
As can be seen from the above embodiments, the present invention provide aviation alloyed aluminium preparation technology can carry heavy alloyed
Ingot casting shaping rate and flaw detection qualification rate.
The above is only the preferred embodiment of the present invention it is noted that ordinary skill people for the art
For member, under the premise without departing from the principles of the invention, some improvements and modifications can also be made, these improvements and modifications also should
It is considered as protection scope of the present invention.
Claims (6)
1. a kind of preparation technology of aviation alloyed aluminium ingot casting, comprises the following steps：
A) carry out melting by after the mixing of Cu source, Mg source, Zn source, Ti source, Zr source and Al source, obtain melting thing, the temperature of described melting
Spend for 800～1050 DEG C；
B) by described step A) the melting thing that obtains carries out online degasification, on-line filtration and in line thinning successively, located online
Reason product；
C) by described step B) the online treatment product that obtains cast, and obtains aviation alloyed aluminium ingot blank；
When the length of described casting is between 0mm～300mm, the speed of described casting is 8～9mm/min, described casting
During cooling water flow be 10～11m3/h；
As the length ＞ 300mm of described casting, the speed of described casting is increased with the speed of (1mm/min)/50mm, until
The speed of described casting reaches 13～14mm/min, by the flow of cooling water during described casting with (1m3/ h)/50mm
Speed increases, until the flow of described cooling water reaches 19～20m3/h；
D) by described step C) the aviation alloyed aluminium ingot blank that obtains carries out homogenization heat treatment, obtains aviation alloyed aluminium casting
Ingot；Described aviation alloyed aluminium ingot casting includes 7050 aluminium alloy cast ingots and 7A85 aluminium alloy cast ingot.
2. preparation technology according to claim 1 is it is characterised in that described step A) specifically include following steps：
Carry out melting after Cu source, Zn source, Ti source, Zr source and Al source are mixed, after melt all melts, add Mg source and 0-
0.0009% Be, carries out melting, obtains melting thing.
3. preparation technology according to claim 1 is it is characterised in that the temperature of described online degasification is 715～725 DEG C；
The gas flow rate of described online degasification is 25～35L/min；
Described carried out using Al-5Ti-B silk in line thinning.
4. preparation technology according to claim 1 is it is characterised in that the temperature of described casting is 650～770 DEG C.
5. preparation technology according to claim 1 is it is characterised in that the holding temperature of described homogenization heat treatment is 460
～470 DEG C；
The temperature retention time of described homogenization heat treatment is 30～35 hours.
6. the specification that preparation technology as claimed in any one of claims 1 to 5, wherein is obtained is the aluminium alloy cast ingot of Φ 850mm.
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| CN104846242A (en) * | 2015-05-12 | 2015-08-19 | 福建省闽发铝业股份有限公司 | High-strength aluminum alloy |
| CN106521197B (en) * | 2016-11-16 | 2018-07-17 | 山东南山铝业股份有限公司 | A kind of aviation alloyed aluminium and its production technology |
| CN109022962B (en) * | 2018-07-24 | 2019-12-24 | 东北轻合金有限责任公司 | Aviation aluminum alloy flat ingot and manufacturing method thereof |
| CN113430433A (en) * | 2021-08-25 | 2021-09-24 | 中国航发北京航空材料研究院 | Aging treatment method of aluminum alloy component |
| CN113969368A (en) * | 2021-10-25 | 2022-01-25 | 西南铝业（集团）有限责任公司 | 7-series aluminum alloy ingot for large-size die forgings and control method of hydrogen content of 7-series aluminum alloy ingot |
| CN115740376B (en) * | 2022-11-30 | 2025-01-28 | 昆明理工大学 | A method for controlling the precipitation phase structure of aluminum-zirconium master alloy |
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