CN104404415A - 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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- CN104404415A CN104404415A CN201410762704.2A CN201410762704A CN104404415A CN 104404415 A CN104404415 A CN 104404415A CN 201410762704 A CN201410762704 A CN 201410762704A CN 104404415 A CN104404415 A CN 104404415A
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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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- 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
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, particularly relate to a kind of preparation technology and aluminium alloy cast ingot of aviation alloyed aluminium ingot casting.
Background technology
Aluminium alloy take aluminium as the alloy general name of matrix element, and the alloying element mainly comprised has copper, silicon, magnesium, zinc, manganese, also comprises the alloying elements such as nickel, iron, titanium, chromium, lithium.The density of aluminium alloy is low, but strength ratio is higher, close to or exceed high-quality steel, plasticity is good, various section bar can be processed into, have excellent electroconductibility, thermal conductivity and corrosion stability, be a most widely used class nonferrous materials in Aeronautics and Astronautics, automobile, machinofacture, boats and ships and chemical industry, its usage quantity is only second to steel.
Usually, the aluminium alloy of more than yield strength 500MPa is called as ultrahigh-strength aluminum alloy, they are main heat-treatable strengthened aluminium alloy (being called for short 7xxx line aluminium alloy) with AL-Zn-Mg-Cu system and Al-Zn-Mg, since the middle of last century, in order to improve the mechanical property of Al-Zn-Mg line aluminium alloy, and solve the serious stress corrosion problem existed in high zinc, high-magnesium aluminum alloy, in such aluminium alloy, add the elements such as Cu, Cr, Mn abroad, thereby produce a series of new A L-Zn-Mg-Cu super-hard aluminum alloys.It is owing to having high specific tenacity and hardness, good hot workability, excellent welding property, high fracture toughness, and the advantage such as high anti-stress-corrosion ability and be widely used in aerospace field, and becomes one of material important in this field.
Wherein, 7A85 aluminium alloy (the external trade mark is 7085) in 7xxx line aluminium alloy and 7050 aluminium alloys are the ideal structured material of air system, novel 7A85 aluminium alloy is mainly used in the important primary structure member of the thick large gauge of airliner, as wing spar, fuselage reinforcing frame, gear support beam etc.; 7050 aluminium alloys for the manufacture of the main bearing member of aircraft, as fuselage ring, dividing plate, wing wallboard, spar, rib, gear support beam etc.
Production technique comprises melting, online treatment and casting still, and the ingot blank flaw detection qualification rate that the preparation technology of existing 7A85 aluminium alloy and 7050 aluminium alloys produces is lower.
Summary of the invention
The object of the present invention is to provide a kind of preparation technology and aluminium alloy cast ingot of aviation alloyed aluminium ingot casting, the aluminium alloy cast ingot flaw detection qualification rate that the preparation technology of aviation alloyed aluminium ingot casting provided by the invention obtains is higher.
The invention provides a kind of preparation technology of aviation alloyed aluminium ingot casting, comprise the following steps:
A) carry out melting by after Cu source, Mg source, Zn source, Ti source, Zr source and the mixing of Al source, obtain melting thing;
B) by described steps A) the melting thing that obtains carries out online degasification, on-line filtration and at line thinning successively, obtains online treatment product;
C) by described step B) the online treatment product that obtains casts, and obtain 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 that obtains carries out homogenizing thermal treatment, obtains aviation alloyed aluminium ingot casting;
Described aviation alloyed aluminium ingot casting comprises 7050 aluminium alloy cast ingots and 7A85 aluminium alloy cast ingot.
Preferably, described steps A) specifically comprise the following steps:
Carry out melting by after Cu source, Zn source, Ti source, Zr source and the mixing of Al source, after melt all melts, add the Be of Mg source and 0-0.0009%, carry out melting, obtain 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;
Describedly Al-5Ti-B silk is adopted to carry out at 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 water coolant is 10 ~ 20m
3/ h.
Preferably, when the length of described casting is between 0mm ~ 300mm, in described castingprocesses, the flow of water coolant is 10 ~ 11m
3/ h;
As the length > 300mm of described casting, by the flow of water coolant in described castingprocesses with (1m
3/ h)/50mm speed increase, until the flow of described water coolant reaches 19 ~ 20m
3/ h.
Preferably, the heat treated holding temperature of described homogenizing is 460 ~ 470 DEG C;
The heat treated soaking time of described homogenizing is 30 ~ 35 hours.
The invention provides the aluminium alloy cast ingot that specification that the preparation technology as described in technique scheme obtains is Φ 850mm.
The invention provides a kind of preparation technology of aviation alloyed aluminium ingot casting, comprise the following steps: A) carry out melting by after Cu source, Mg source, Zn source, Ti source, Zr source and the mixing of Al source, obtain melting thing; B) by described steps A) the melting thing that obtains carries out online degasification, on-line filtration and at line thinning successively, obtains online treatment product; C) by described step B) the online treatment product that obtains casts, and obtain 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 that obtains carries out homogenizing thermal treatment, obtains aviation alloyed aluminium ingot casting; Described aviation alloyed aluminium ingot casting comprises 7050 aluminium alloy cast ingots and 7A85 aluminium alloy cast ingot.Preparation technology provided by the invention adopts suitable casting speed, can prevent molten aluminium when casting from revealing, and reduces the crackle tendency at ingot casting center and the drawing crack tendency on ingot casting surface, improves the flaw detection qualification rate of aluminium alloy.Experimental result shows, the flaw detection qualification rate of 7050 aluminium alloy cast ingots that the preparation technology of aviation aluminium provided by the invention obtains and 7A85 aluminium alloy cast ingot is 97 ~ 99%.
Accompanying drawing explanation
In order to be illustrated more clearly in the embodiment of the present invention or technical scheme of the prior art, be briefly described to the accompanying drawing used required in embodiment or description of the prior art below, apparently, accompanying drawing in the following describes is only embodiments of the invention, for those of ordinary skill in the art, under the prerequisite not paying creative work, other accompanying drawing can also be obtained according to the accompanying drawing provided.
Fig. 1 be the top layer of the 7A85 aluminium alloy cast ingot gate part that the embodiment of the present invention 1 obtains 50 × under high power detect figure;
Fig. 2 be the top layer of the 7A85 aluminium alloy cast ingot gate part that the embodiment of the present invention 1 obtains 200 × under high power detect figure;
Fig. 3 be 1/4 of the 7A85 aluminium alloy cast ingot gate part that the embodiment of the present invention 1 obtains be in 50 × under high power detect figure;
Fig. 4 be 1/4 of the 7A85 aluminium alloy cast ingot gate part that the embodiment of the present invention 1 obtains be in 200 × under high power detect figure;
Fig. 5 be the heart portion of the 7A85 aluminium alloy cast ingot gate part that the embodiment of the present invention 1 obtains 50 × under high power detect figure;
Fig. 6 be the heart portion of the 7A85 aluminium alloy cast ingot gate part that the embodiment of the present invention 1 obtains 200 × under high power detect figure;
Fig. 7 is the 7A85 bottom of aluminum alloy ingot top layer that obtains of the embodiment of the present invention 1 50 × under high power detect figure;
Fig. 8 is the 7A85 bottom of aluminum alloy ingot top layer that obtains of the embodiment of the present invention 1 200 × under high power detect figure;
Fig. 9 be 1/4 of the 7A85 bottom of aluminum alloy ingot that the embodiment of the present invention 1 obtains be in 50 × under high power detect figure;
Figure 10 be 7A85 bottom of aluminum alloy ingot 1/4 that the embodiment of the present invention 1 obtains be in 200 × under high power detect figure;
Figure 11 be the heart portion of the 7A85 bottom of aluminum alloy ingot that the embodiment of the present invention 1 obtains 50 × under high power detect figure;
Figure 12 be the heart portion of the 7A85 bottom of aluminum alloy ingot that the embodiment of the present invention 1 obtains 200 × under high power detect figure.
Embodiment
The invention provides a kind of preparation technology of aviation alloyed aluminium ingot casting, comprise the following steps:
A) carry out melting by after Cu source, Mg source, Zn source, Ti source, Zr source and the mixing of Al source, obtain melting thing;
B) by described steps A) the melting thing that obtains carries out online degasification, on-line filtration and at line thinning successively, obtains online treatment product;
C) by described step B) the online treatment product that obtains casts, and obtain aviation alloyed aluminium ingot blank, the speed of described casting is 8 ~ 14mm/min;
D) by described step C) the aviation alloyed aluminium ingot blank that obtains carries out homogenizing thermal treatment, obtains aviation alloyed aluminium ingot casting;
Described aviation alloyed aluminium ingot casting comprises 7050 aluminium alloy cast ingots and 7A85 aluminium alloy cast ingot.
The flaw detection qualification rate of 7050 aluminium alloy cast ingots that preparation technology provided by the invention obtains and 7A85 aluminium alloy cast ingot is higher, can reach 97 ~ 99%.
The present invention carries out melting by after Cu source, Mg source, Zn source, Ti source, Zr source and the mixing of Al source, obtains melting thing; The present invention preferably carries out described melting in smelting furnace, the present invention is preferably first sprinkled into No. two solvents before shove charge in described smelting furnace, is loaded in smelting furnace in Cu source, Zn source, Ti source, Zr source and Al source, carries out melting, after softening the staying of melt is flat, in stove, be 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 added and the Be of 0-0.0009%, add rear employing No. two solvent powder to cover, melting after stirring, obtains melting thing.
When shove charge, should be undertaken in principle by order from small to large, be about to first fill dead small, refill bulk material, be contained at the middle and upper levels simultaneously by master alloy high for fusing point, the metal of easy scaling loss is contained in middle level.
In the present invention, the massfraction of described Cu in described raw material is 1.3 ~ 2.6%, is preferably 1.5 ~ 2.3%; The present invention preferably adopts pure Cu plate to be that described melting is carried out in Cu source, massfraction >=99.95% of Cu in described pure Cu plate.
In the present invention, the massfraction of described Zn in raw material used is 5.7 ~ 8.0%, is preferably 6.0 ~ 7.5%, is more preferably 6.5 ~ 7.0%; The present invention preferably adopts pure zinc ingot to be that described melting is carried out in Zn source, and in described pure zinc ingot, the massfraction of Zn preferably >=99.99%.
In the present invention, the massfraction of described Ti in raw material used is 0 ~ 0.06%, is preferably 0 ~ 0.03%; Described Ti can crystal grain thinning and prevent ingot casting crackle, and the present invention preferably adopts Al-Ti master alloy to be that described melting is carried out in Ti source, and in described Al-Ti master alloy, the massfraction of Ti is preferably 3 ~ 5%, is more preferably 4%.
In the present invention, the massfraction of described Zr in raw material used is 0.08 ~ 0.15%, is preferably 0.1 ~ 0.13%; The present invention preferably adopts Al-Zr master alloy to be that described melting is carried out in Zr source, and in described Al-Zr master alloy, the massfraction of Zr is preferably 3 ~ 5%, is more preferably 4%.
In the present invention, the massfraction of described Mg in raw material used is 1.2 ~ 2.6%, is preferably 1.5 ~ 2.5%; The present invention preferably adopts pure Mg ingot to be that described melting is carried out in Mg source, and in described pure Mg ingot, the massfraction of Mg preferably >=99.95%.
In the present invention, the massfraction of described Be is 0-0.0009%
In the present invention, the massfraction sum of the massfraction of described Al in raw material used and other components is 100%, and the present invention preferably adopts pure Al ingot to be that described melting is carried out in Al source, and in described pure Al ingot, the massfraction of Al preferably >=99.7%.
In the present invention, described No. two solvent powder are commercially available prod, comparatively standard, are calculated in mass percent: KCl:32-40%, MgCl
2: 38-46%, BaCl
2: 5-8%, model is No. two, and the company of home sale barium fluxing agent powder is very many, large-scale aluminium manufacturer also self manufacture, and as southwestern aluminium, each usage quantity is preferably 0.5 ~ 2% of above-mentioned raw materials total amount, is more preferably 1%.
In the present invention, described aviation alloyed aluminium ingot casting comprises 7050 aluminium alloy cast ingots and 7A85 aluminium alloy cast ingot, the chemical composition contained by aluminium alloy of the different trade mark and the content of chemical composition different, as, in massfraction, in 7050 aluminium alloys, comprise the Cu of 2.3%, 2.3% Mg, Zn, the Ti of 0.02% of 6.2%, the Al of the Zr of 0.12% and surplus; In 7A85 aluminium alloy, comprise the Cu of 1.7%, Mg, the Zn of 7.6% of 1.7%, the Al of the Zr of 0.12% and surplus.
In the present invention, in described fusion process, the fire box temperature of melting is preferably 800 ~ 1050 DEG C, is more preferably 900 ~ 1000 DEG C, and in described melting, the temperature of melt is preferably 600 ~ 770 DEG C, is more preferably 650 ~ 750 DEG C; The time of described melting is preferably 20 ~ 60min, is more preferably 30 ~ 50min.
After completing described melting, the present invention preferably samples the melt obtained, to analyze bath composition, then carries out corresponding composition adjustment according to the content requirement of above-mentioned each composition, and the method for described adjustment is method well known to those skilled in the art.Concrete, determine whether water down or feed supplement according to censorship result, to water down or feed supplement is carried out according to quantity as follows:
If produce 7A85 aluminium alloy cast ingot length 4200mm, 1 casting 4, consider oxidization burning loss 5%, ingot casting specification Φ 650, this alloy density is 2800kg/m
3, then total charging capacity=π × 0.652/4 × 4.2 × 4 × (1+5%) × 2800 ≈ 17400kg is calculated.
For Cu element, if Cu element on-the-spot sample analysis value is 1.3%, need 1.6% be mended,
Then need Al-Cu master alloy weight=17400 × (the 1.6%-1.3%)/40% ≈ 130kg mending content 40%;
If Cu element on-the-spot sample analysis value 2.1%, need water down to 1.9%,
Then need AL99.70 ingot total amount=17400 × (the 2.1%-1.9%)/1.9% ≈ 180kg watered down.
Note feed supplement or before watering down, suitably should improve more than melt temperature to 750 DEG C, and the metal added or master alloy should be dry, prevent accidents such as blowing out.
The present invention preferably samples at the middle melt of fire door, and adopts described No. two solvent powder to cover after sampling.
After completing composition adjustment, the present invention preferably adopts refining pipe to carry out argon gas refining in stove, and the time of described refining is preferably 15 ~ 30min, is more preferably 20min, and the temperature of described refining is preferably 730 ~ 750 DEG C, is more preferably 740 DEG C; During described refining, the height of bubble should not more than 80mm.
After completing described refining, melt preferably leaves standstill by the present invention, obtains melting thing, the described standing time preferably >=25min.
After obtaining melting thing, described melting thing is carried out online degasification, on-line filtration and at line thinning by the present invention successively, obtains online treatment product.The present invention adopts twin-stage to rotate degasification molten aluminium in-line purification technology, solves the difficult problem that traditional Ф 850mm circle ingot casting hydrogen richness is higher, restrict forging goods following process quality in kind and performance boost.
In the present invention, described online degasification preferably adopts two rotors refinery by de-gassing device, and the flow of described refining gas is preferably 25 ~ 35L/min, is more preferably 30L/min; The temperature of described refining is preferably 715 ~ 725 DEG C, is more preferably 720 DEG C; The rotating speed of described rotor is preferably 290 ~ 310rpm, is more preferably 295 ~ 305rpm.
In the present invention, described on-line filtration preferably adopts single-stage 30ppi ceramic filter plate to filter; Describedly preferably adopt Al-5Ti-B silk at line thinning.
After completing online treatment, the online treatment product obtained is cast by the present invention, obtains aviation alloyed aluminium ingot blank, and in the present invention, the speed of described casting is 8 ~ 14mm/min, is preferably 9 ~ 13mm/min, is more preferably 10 ~ 12mm/min; The temperature of described casting is preferably 650 ~ 770 DEG C; In described castingprocesses, the flow of water coolant is preferably 10 ~ 20m
3/ h.In the present invention, at first, described casting speed is preferably 8 ~ 9mm/min, is more preferably 8mm/min in described casting, and described cooling water flow is preferably 10 ~ 11m
3/ h, is more preferably 10m
3/ h; After casting length reaches 300mm, described casting speed is increased with the speed of (1mm/min)/50mm, until described casting speed reaches 13 ~ 14mm/min, is more preferably 14mm/min; The flow of described water coolant is with (1m
3/ h) (after the length of namely casting reaches 300mm, casting length often increases 50mm to/50mm, and discharge increases 1m
3/ h) speed increase, until the flow of described water coolant reaches 19 ~ 20m
3/ h.Cooling water flow is too high or too low, casting speed is crossed when all can make casting slowly and produced molten aluminium leakage, causes castingprocesses to carry out; Casting speed is too fast makes the increase of ingot casting centre burst tendency, the increase of ingot casting surface generation drawing crack tendency, even produces molten aluminium bleedout phenomenon time serious.The present invention adopts suitable casting speed to cast, and to reduce centre burst tendency, ingot casting also there will not be Serious Cold every generation transverse crack.The present invention adopts the water-cooling method strengthened gradually, and due to one time, water-cooled is more weak, and liquid cave is more shallow, be not easy to produce centre burst ingot casting, secondary water-cooled is strengthened relatively, and speed of cooling improves greatly, make the aluminium alloy cast ingot dense internal organization obtained, improve ingot casting ratio of briquetting and internal metallurgical quality.
The present invention preferably still has when 1/3 at gate part liquid and cuts off the water, and stops, complete described casting when gate part will depart from crystallizer at once.
If without fine aluminium shop fixtures technique when adopting prior art casting 7A85,7050 alloy large gauge billet, easily crack bottom ingot casting, an even whole entire crack.The present invention adopts paving false uphill casting technology for making, without the need to fine aluminium shop fixtures, exempts from wiper and scrapes water tempering, is conducive to simplifying casting process, reduces production cost.
After completing described casting, the present invention preferably anneals to the ingot casting obtained, and to remove stress, the temperature of described annealing is preferably 350 ~ 450 DEG C, is more preferably 380 ~ 420 DEG C; The time of described annealing is preferably 6 ~ 10 hours, is more preferably 7 ~ 9 hours.
After obtaining aviation alloyed aluminium ingot blank, the aviation alloyed aluminium ingot blank obtained is carried out homogenizing thermal treatment by the present invention, obtain aviation alloyed aluminium ingot casting, 7A85,7050 alloys dissolve in matrix mainly through strengthening element Zn, Mg, Cu solid solution, form supersaturated solid solution, the precipitation strength phase of diffusion-precipitation distribution during timeliness and obtain superior performance, and more residually not moltenly will be unfavorable for the raising of performance.Meanwhile, large gauge, high-alloying ingot casting also make alloying constituent segregation serious, therefore work as important to the homogenizing heat treatment phase that ingot casting carries out.
In the present invention, the Al separated out in Homogenization Process
3the overall performance of Zr particle alloy has material impact, the Al of the tiny distribution of disperse
3zr particle effectively can suppress crystal boundary migration, retains more Deformation structure after impelling solid solution in alloy, improves alloy mechanical property and anti-stress corrosion performance.Al near crystal boundary
3the microscopic appearance of Zr particle is observed and is shown, introduces slow rate temperature-rise period to Al
3zr particle dispersion is separated out has vital role.Under normal circumstances, the Al in Homogenization Process
3it is precipitation precipitation process that Zr particle is separated out, not only relevant with system free energy difference, is also associated with the distribution of Zr element.During alloy graining, Zr atom dilution near dendrite has a common boundary in the enrichment of dendrite center in ingot casting, although can by intracrystalline to grain boundary decision at Homogenization Process Zr atom, but the precipitation peak value of Al3Zr particle is at high-temperature area, adopt single-stage or be rapidly heated Homogenization Treatment time, Zr atom often has little time diffusion just as Al
3zr particle is separated out and is grown up.Therefore the Homogenization Treatment of rapid heating condition, Al
3zr particle distribution density has the trend obviously reduced gradually from intracrystalline to crystal boundary, and the nothing existed near crystal boundary in a big way separates out district.
In the present invention, before homogenizing thermal treatment is carried out in the shove charge of described aviation alloyed aluminium ingot casting, furnace temperature≤350 DEG C should be guaranteed, the present invention preferably heats with the Heating temperature of 490 ~ 500 DEG C, until enter holding stage when in-furnace temperature reaches 460 ~ 470 DEG C, the temperature of described insulation is preferably 460 ~ 470 DEG C, is more preferably 465 DEG C; Described soaking time is 30 ~ 35 hours, is more preferably 32 hours.
In order to improve the over-all properties of aviation alloyed aluminium following process material, high-power blower can be adopted when coming out of the stove to cool the following air cooling again of ingot casting to 200 DEG C, this kind of operation can slow down the alligatoring containing Zr particle, improves the effect of its suppression recrystallize.
After completing homogenizing thermal treatment, the present invention preferably carries out aftertreatment to the aluminium alloy cast ingot that described homogenizing thermal treatment obtains, described aftertreatment comprises ingot casting sawing, processing and detection, and described aftertreatment can process according to the need of production of reality, and the present invention does not do special restriction.
Present invention also offers the aluminium alloy cast ingot that a kind of specification is Φ 850mm, prepare according to the preparation technology described in technique scheme, flaw detection qualification rate is higher.Aluminium alloy cast ingot provided by the invention comprises 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 massfraction: Cu:2.0 ~ 2.6%; Mg:1.9 ~ 2.6%; Zn:5.7 ~ 6.7%; Ti:0 ~ 0.06%; Zr:0.08 ~ 0.15%; Surplus is Al; The mass ratio of described Zn and Mg is (2.5 ~ 3.0): 1.
The present invention, by the optimization of Cu content and Zn/Mg ratio and accurately control, improves the intensity of 7050 aluminium alloys.
7050 aluminium alloys provided by the invention comprise Cu, and the massfraction of described Cu is 2.0 ~ 2.6%, are preferably 2.1 ~ 2.3%, are more preferably 2.2%; The present invention preferably adopts pure Cu plate to carry out described melting, massfraction >=99.95% of Cu in described pure Cu plate.
7050 aluminium alloys provided by the invention comprise Mg, and the massfraction of described Mg is 1.9 ~ 2.6%, are preferably 2.1 ~ 2.4%, are more preferably 2.3%.The present invention preferably adopts pure Mg ingot to carry out described melting, and in described pure Mg ingot, the massfraction of Mg preferably >=99.95%.
7050 aluminium alloys provided by the invention comprise Zn, and the massfraction of described Zn is 5.7 ~ 6.7%, are preferably 6.0 ~ 6.5%, are more preferably 6.2%.In the present invention, the mass ratio of described Zn and Mg is (2.5 ~ 3.0): 1, is preferably 2.7:1.The present invention is by the accurate control to the mass ratio of Zn/Mg, and 7050 aluminium alloys that the present invention is obtained have good intensity and toughness.The present invention preferably adopts pure zinc ingot to carry out described melting, and in described pure zinc ingot, the massfraction of Zn preferably >=99.99%.
7050 aluminium alloys provided by the invention comprise Ti, and described Ti can crystal grain thinning and prevent ingot casting crackle.In the present invention, the massfraction of described Ti is 0 ~ 0.06%, is preferably 0.01 ~ 0.03%, is more preferably 0.02%.The present invention preferably adopts Al-Ti master alloy to carry out described melting, and in described Al-Ti master alloy, the massfraction of Ti is preferably 3 ~ 5%, is more preferably 4%.
7050 aluminium alloys provided by the invention comprise Zr, and the massfraction of described Zr is preferably 0.08 ~ 0.15%, are preferably 0.10 ~ 0.13%, are more preferably 0.12%.The present invention preferably adopts Al-Zr master alloy to carry out described melting, and in described Al-Zr master alloy, the massfraction of Zr is preferably 3 ~ 5%, is more preferably 4%.Zr is as the important Addition ofelements in alloy, main with compd A l between the granulated metal of small and dispersed distribution in the material
3zr form exists.This intermetallic compound possesses two kinds of forms: a kind of is the Al directly separated out from melt
3zr primary phase, has the effect of refinement as-cast grain; Another kind is the granular Al of the small and dispersed distribution that in subsequent thermal processing process, (as ingot homogenization) is decomposed to form
3zr secondary phase, the recrystallize tendency in strongly inhibited subsequent thermal processing process, and as the original position particle in ag(e)ing process, the precipitation distribution of η phase, state are played an important role.
In the present invention, the massfraction sum of the massfraction of described Al in raw material used and other components is 100%, and the present invention preferably adopts pure Al ingot to carry out described melting, and in described pure Al ingot, the massfraction of Al preferably >=99.7%.
In the present invention, the aluminium alloy of described 7050 aluminium alloys to be specification be Φ 850mm.
In the present invention, in described 7050 aluminium alloys, also comprise some impurity, e.g., one or more in Si, Fe, Mn and Cr, massfraction≤0.12% of described Si; Massfraction≤0.15% of described Fe; Massfraction≤0.10% of described Mn; Massfraction≤0.04% of described Cr.
In 7050 aluminium alloys provided by the invention, Zn, Mg, Cu are main alloy elements, Zn, Mg element as the main strengthening element of alloy, mainly in the alloy with solid solution, equilibrium phase η (MgZn
2), T (Al
2mg
3zn
3) and non-equilibrium phase η ' form exist, also there is a certain amount of AlCuFe, S (AlCuMg) phase in alloy in addition.η ' the phase separated out in ag(e)ing process is the main strengthening phase of alloy.Cu major part is dissolved in matrix, plays assisted and strengthened effect, can also reduce the potential difference between intracrystalline and crystal boundary and improve stress corrosion performance.
Aviation alloyed aluminium ingot casting provided by the invention comprises 7A85 aluminium alloy, and described 7A85 aluminium alloy preferably includes the component of following massfraction:
Cu:1.3 ~ 2.0%; Mg:1.2 ~ 1.8%; Zn:7.0 ~ 8.0%; Zr:0.08 ~ 0.15%; Surplus is Al; The mass ratio of described Zn and Mg is (4.5 ~ 5.0): 1.
The present invention, by the optimization of Cu content and Zn/Mg ratio and accurately control, improves the intensity of 7A85 aluminium alloy.
7A85 aluminium alloy provided by the invention comprises Cu, and the massfraction of described Cu is 1.3 ~ 2.0%, is preferably 1.5 ~ 1.8%, is more preferably 1.7%; The present invention preferably adopts pure Cu plate to carry out described melting, massfraction >=99.95% of Cu in described pure Cu plate.
7A85 aluminium alloy provided by the invention comprises Mg, and the massfraction of described Mg is 1.2 ~ 1.8%, is preferably 1.5 ~ 1.7%, is more preferably 1.6 ~ 1.7%.The present invention preferably adopts pure Mg ingot to carry out described melting, and in described pure Mg ingot, the massfraction of Mg preferably >=99.95%.
7A85 aluminium alloy provided by the invention comprises Zn, and the massfraction of described Zn is 7.0 ~ 8.0%, is preferably 7.2 ~ 7.8%, is more preferably 7.6%.In the present invention, the mass ratio of described Zn and Mg is (4.5 ~ 5.0): 1, is preferably 4.8:1.The present invention is by the accurate control to the mass ratio of Zn/Mg, and the 7A85 aluminium alloy that the present invention is obtained has good intensity and toughness.The present invention preferably adopts pure zinc ingot to carry out described melting, and in described pure zinc ingot, the massfraction of Zn preferably >=99.99%.
7A85 aluminium alloy provided by the invention comprises Zr, and the massfraction of described Zr is preferably 0.08 ~ 0.15%, is preferably 0.10 ~ 0.13%, is more preferably 0.12%.The present invention preferably adopts Al-Zr master alloy to carry out described melting, and in described Al-Zr master alloy, the massfraction of Zr is preferably 3 ~ 5%, is more preferably 4%.Zr is as the important Addition ofelements in alloy, main with compd A l between the granulated metal of small and dispersed distribution in the material
3zr form exists.This intermetallic compound possesses two kinds of forms: a kind of is the Al directly separated out from melt
3zr primary phase, has the effect of refinement as-cast grain; Another kind is the granular Al of the small and dispersed distribution that in subsequent thermal processing process, (as ingot homogenization) is decomposed to form
3zr secondary phase, the recrystallize tendency in strongly inhibited subsequent thermal processing process, and as the original position particle in ag(e)ing process, the precipitation distribution of η phase, state are played an important role.
In the present invention, the massfraction sum of the massfraction of described Al in raw material used and other components is 100%, and the present invention preferably adopts pure Al ingot to carry out described melting, and in described pure Al ingot, the massfraction of Al preferably >=99.7%.
In the present invention, the aluminium alloy of described 7A85 aluminium alloy to be specification be Φ 850mm.
In the present invention, in described 7A85 aluminium alloy, also comprise some impurity, e.g., one or more in Si, Fe, Mn, Ti and Cr, massfraction≤0.06% of described Si; Massfraction≤0.08% of described Fe; Massfraction≤0.04% of described Mn; Massfraction≤0.04% of described Cr; Massfraction≤0.06% of Ti.
In 7A85 aluminium alloy provided by the invention, Zn, Mg, Cu are main alloy elements, Zn, Mg element as the main strengthening element of alloy, mainly in the alloy with solid solution, equilibrium phase η (MgZn
2), T (Al
2mg
3zn
3) and non-equilibrium phase η ' form exist, also there is a certain amount of AlCuFe, S (AlCuMg) phase in alloy in addition.η ' the phase separated out in ag(e)ing process is the main strengthening phase of alloy.Cu major part is dissolved in matrix, plays assisted and strengthened effect, can also reduce the potential difference between intracrystalline and crystal boundary and improve stress corrosion performance.
The present invention is out of shape Al alloys andMg alloys product supersonic testing method according to GB/T 6519-2013 and has carried out carrying out flaw detection to the aviation alloyed aluminium that the present invention obtains, and result shows, the flaw detection qualification rate of aviation alloyed aluminium provided by the invention is 97 ~ 99%.
The present invention has carried out intensity detection according to GB/T228 " metallic substance tensile testing at ambient temperature " to the aviation alloyed aluminium that the present invention obtains, and result shows, the intensity of aviation alloyed aluminium provided by the invention is 520MPa.
The present invention is out of shape the Al and Alalloy goods microstructure method of inspection according to GB/T 3246.1-2000 and has carried out high power detection to the aviation alloyed aluminium that the present invention obtains.
The invention provides a kind of preparation technology of aviation alloyed aluminium ingot casting, comprise the following steps: A) carry out melting by after Cu source, Mg source, Zn source, Ti source, Zr source and the mixing of Al source, obtain melting thing; B) by described steps A) the melting thing that obtains carries out online degasification, on-line filtration and at line thinning successively, obtains online treatment product; C) by described step B) the online treatment product that obtains casts, and obtain 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 that obtains carries out homogenizing thermal treatment, obtains aviation alloyed aluminium ingot casting; Described aviation alloyed aluminium ingot casting comprises 7050 aluminium alloy cast ingots and 7A85 aluminium alloy cast ingot.Preparation technology provided by the invention adopts suitable casting speed, can prevent molten aluminium when casting from revealing, and reduces the crackle tendency at ingot casting center and the drawing crack tendency on ingot casting surface, improves the flaw detection qualification rate of aluminium alloy.Experimental result shows, the flaw detection qualification rate of 7050 aluminium alloys that the preparation technology of aviation aluminium provided by the invention obtains and 7A85 aluminium alloy is 97 ~ 99%.
In order to further illustrate the present invention, below in conjunction with embodiment, the preparation technology of a kind of aviation alloyed aluminium ingot casting provided by the invention and aluminium alloy cast ingot thereof being described in detail, but can not limiting the scope of the present invention being understood as.
In the examples below, starting material used meet following requirement:
Remelted aluminum ingot: Al >=99.7%; Remelting magnesium ingot: Mg >=99.95%; Electrolytic copper: Cu >=99.95%; Zinc ingot metal: Zn >=99.99%; Master alloy: Al-15Mn, Al-4Cr, Al-4Ti, Al-4Zr, Al-3Be: in above-mentioned all master alloys, Fe, Si≤0.6%, other≤0.1%.Al-10Fe:Si≤0.6%, other≤0.1%.At line thinning: Al-5Ti-B Φ 9.5mm silk.
Subsidiary material used meet following requirement:
Liquid argon: purity>=99.98%, H
2o≤10ppm, [H
2]≤5ppm, [O
2]≤10ppm; 2# flux: technical grade; On-line filtration: 30ppi ceramic filter plate.
Reasonably combined use low iron sial ingot and one-level waste material own is answered during alloying ingredient, high-precision aluminium ingot consumption >=50%, one-level waste material consumption requires≤30%, requires that starting material surface cleaning is clean during batching, copper, magnesium, zinc element are directly with pure metal batching, and other are prepared burden with master alloy.
Embodiment 1
Production extrusion ingot length 4200mm, ingot casting specification are the 7A85 aluminium alloy of Φ 850.1 casting 4, consider oxidization burning loss 5%, this alloy density is 2800kg/m
3, then total charging capacity=π × 0.85 is calculated
2/ 4 × 4.2 × 4 × (1+5%) × 2800 ≈ 28400kg.
The 2# solvent powder of 65kg is evenly sprinkled in smelting furnace, then pure for 482kg Cu plate, the pure Zn ingot of 2156kg, 142kgAl-Ti master alloy, 851kgAl-Zr master alloy and 24287kgAL ingot are carried out shove charge by order from small to large, be about to first fill dead small, refill bulk material, be contained at the middle and upper levels by master alloy high for fusing point, the metal of easy scaling loss is contained in middle level simultaneously.The fire box temperature of smelting furnace controls at≤1050 DEG C, and melt temperature controls at≤770 DEG C, when melt is softening stay and change flat after, in stove, be evenly sprinkled into the 2# ground flux of 130kg, and stir metal in good time.
After furnace charge has all melted, when melt temperature reaches about 730 DEG C, add the Al-Be master alloy of 482kg Mg ingot and 8.5kg.Adition process and add rear 89kg2# ground flux cover, usage quantity is as the criterion to cover completely.Thoroughly should stir after adding, and temperature adjustment is stabilized in about 740 DEG C, after about spending 20 minutes, carry out stokehold sampling.
Sampling must be carried out at melt in the middle of fire door, carries out composition adjustment according to the control overflow in both analysis result and technique scheme.
After composition adjustment completes, adopt refining pipe to carry out argon gas refining in stove, refining time 20 minutes, refining temperature about 740 DEG C, during refining, bubble height should not more than 80mm.
Should leave standstill after refining completes, time of repose at least 25 minutes.
Adopt two rotors refinery by de-gassing device to carry out online degasification the melt after leaving standstill, refining gas consumption is 30L/min, and refining temperature is 720 ± 5 DEG C, and rotor speed is 300 ± 5rpm; Then adopt single-stage 30ppi ceramic filter plate to carry out on-line filtration, when changing screen plate, require the integrity of checked filter plate, and ensure to be in place, carefully put mass, and suitably toast; Then add Al-5Ti-B silk according to the amount of 1.5kg/t, carry out at line thinning.
After completing online treatment, cast by melt, casting temp is 735 DEG C, and when casting starts, having cast vehicle speed is 8mm/min, and cooling water flow is 10m
3/ h, after length to be cast reaches 300mm, by casting speed with the increasing amount adjustment of (1mm/min)/50mm to 14mm/min, by cooling water flow with (1m
3/ h) increasing amount adjustment of/50mm is to 20m
3/ h.
Cut off the water when gate part liquid still has when 1/3 during casting ending, stop when gate part will depart from crystallizer at once, forbid water droplet to gate part.
After having cast, carrying out homogenizing thermal treatment by casting the ingot blank obtained, with the Heating temperature of 495 DEG C heating, entering insulation after being heated to 465 DEG C, being incubated 32 hours, completing homogenizing thermal treatment.
Then anneal 8 hours at 360 DEG C, then carry out sawing accordingly to ingot casting, sawing gate part and bottom all about 350mm, obtains 7A85 aluminium alloy.Casting rate is 93%.
The present invention carries out carrying out flaw detection according to technique scheme to the 7A85 aluminium alloy that the present invention obtains, and result shows, the flaw detection qualification rate of the 7A85 aluminium alloy that the present embodiment obtains is 99%.
The present invention has carried out high power detection according to the gate part of technique scheme to the 7A85 aluminium alloy that the present embodiment obtains, result as shown in figs. 1 to 6, Fig. 1 be the top layer of the 7A85 aluminium alloy cast ingot gate part that the embodiment of the present invention 1 obtains 50 × under high power detect figure; Fig. 2 be the top layer of the 7A85 aluminium alloy cast ingot gate part that the embodiment of the present invention 1 obtains 200 × under high power detect figure; Fig. 3 be 1/4 of the 7A85 aluminium alloy cast ingot gate part that the embodiment of the present invention 1 obtains be in 50 × under high power detect figure; Fig. 4 be 1/4 of the 7A85 aluminium alloy cast ingot gate part that the embodiment of the present invention 1 obtains be in 200 × under high power detect figure; Fig. 5 be the heart portion of the 7A85 aluminium alloy cast ingot gate part that the embodiment of the present invention 1 obtains 50 × under high power detect figure; Fig. 6 be the heart portion of the 7A85 aluminium alloy cast ingot gate part that the embodiment of the present invention 1 obtains 200 × under high power detect figure.As can be seen from Fig. 1 ~ 6, the 7A85 aluminum alloy organization that the present embodiment obtains is fine and close, and homogeneity is better.
The present invention has carried out high power detection according to the bottom of technique scheme to the 7A85 aluminium alloy that the present embodiment obtains, result as shown in Fig. 7 ~ 12, Fig. 7 is the 7A85 bottom of aluminum alloy ingot top layer that obtains of the embodiment of the present invention 1 50 × under high power detect figure; Fig. 8 is the 7A85 bottom of aluminum alloy ingot top layer that obtains of the embodiment of the present invention 1 200 × under high power detect figure; Fig. 9 be 1/4 of the 7A85 bottom of aluminum alloy ingot that the embodiment of the present invention 1 obtains be in 50 × under high power detect figure; Figure 10 be 7A85 bottom of aluminum alloy ingot 1/4 that the embodiment of the present invention 1 obtains be in 200 × under high power detect figure; Figure 11 be the heart portion of the 7A85 bottom of aluminum alloy ingot that the embodiment of the present invention 1 obtains 50 × under high power detect figure; Figure 12 be the heart portion of the 7A85 bottom of aluminum alloy ingot that the embodiment of the present invention 1 obtains 200 × under high power detect figure.As can be seen from Fig. 7 ~ 12, the 7A85 aluminum alloy organization that the present embodiment obtains is fine and close, and homogeneity is better.
Embodiment 2
Production extrusion ingot length 4200mm, ingot casting specification are the 7A85 aluminium alloy of Φ 850.1 casting 4, consider oxidization burning loss 5%, this alloy density is 2800kg/m
3, then total charging capacity=π × 0.85 is calculated
2/ 4 × 4.2 × 4 × (1+5%) × 2800 ≈ 28400kg.
The 2# solvent powder of 65kg is evenly sprinkled in smelting furnace, then pure for 460kg Cu plate, the pure Zn ingot of 2059kg, 135kgAl-Ti master alloy, 812kgAl-Zr master alloy and 24474kgAL ingot are carried out shove charge by order from small to large, be about to first fill dead small, refill bulk material, be contained at the middle and upper levels by master alloy high for fusing point, the metal of easy scaling loss is contained in middle level simultaneously.The fire box temperature of smelting furnace controls at≤1050 DEG C, and melt temperature controls at≤770 DEG C, when melt is softening stay and change flat after, in stove, be evenly sprinkled into the 2# ground flux of 130kg, and stir metal in good time.
After furnace charge has all melted, when melt temperature reaches about 730 DEG C, add the Al-Be master alloy of 460kg Mg ingot and 8.5kg.Adition process and add rear 89kg2# ground flux cover, usage quantity is as the criterion to cover completely.Thoroughly should stir after adding, and temperature adjustment is stabilized in about 740 DEG C, after about spending 20 minutes, carry out stokehold sampling.
Sampling must be carried out at melt in the middle of fire door, carries out composition adjustment according to the control overflow in both analysis result and technique scheme.
After composition adjustment completes, adopt refining pipe to carry out argon gas refining in stove, refining time 20 minutes, refining temperature about 740 DEG C, during refining, bubble height should not more than 80mm.
Should leave standstill after refining completes, time of repose at least 25 minutes.
Adopt two rotors refinery by de-gassing device to carry out online degasification the melt after leaving standstill, refining gas consumption is 30L/min, and refining temperature is 720 ± 5 DEG C, and rotor speed is 300 ± 5rpm; Then adopt single-stage 30ppi ceramic filter plate to carry out on-line filtration, when changing screen plate, require the integrity of checked filter plate, and ensure to be in place, carefully put mass, and suitably toast; Then add Al-5Ti-B silk according to the amount of 1.5kg/t, carry out at line thinning.
After completing online treatment, cast by melt, casting temp is 735 DEG C, and when casting starts, having cast vehicle speed is 8mm/min, and cooling water flow is 10m
3/ h, after length to be cast reaches 300mm, by casting speed with the increasing amount adjustment of (1mm/min)/50mm to 14mm/min, by cooling water flow with (1m
3/ h) increasing amount adjustment of/50mm is to 20m
3/ h.
Cut off the water when gate part liquid still has when 1/3 during casting ending, stop when gate part will depart from crystallizer at once, forbid water droplet to gate part.
After having cast, carrying out homogenizing thermal treatment by casting the ingot blank obtained, with the Heating temperature of 495 DEG C heating, entering insulation after being heated to 465 DEG C, being incubated 32 hours, completing homogenizing thermal treatment.
Then anneal 8 hours at 360 DEG C, then carry out sawing accordingly to ingot casting, sawing gate part and bottom all about 350mm, obtains 7A85 aluminium alloy.Casting rate is 92%.
The present invention carries out carrying out flaw detection according to technique scheme to the 7A85 aluminium alloy that the present invention obtains, and result shows, the flaw detection qualification rate of the 7A85 aluminium alloy that the present embodiment obtains is 99%.
Embodiment 3
Production extrusion ingot length 4000mm, ingot casting specification are 7050 aluminium alloys of Φ 850.1 casting 4, consider oxidization burning loss 5%, this alloy density is 2800kg/m
3, then total charging capacity=π × 0.85 is calculated
2/ 4 × 4.0 × 4 × (1+5%) × 2800 ≈ 26700kg.
The 2# solvent powder of 40kg is evenly sprinkled in smelting furnace, then pure for 614kg Cu plate, the pure Zn ingot of 1654kg, 133kgAl-Ti master alloy, 800kgAl-Zr master alloy and 22855kgAL ingot are carried out shove charge by order from small to large, be about to first fill dead small, refill bulk material, be contained at the middle and upper levels by master alloy high for fusing point, the metal of easy scaling loss is contained in middle level simultaneously.The fire box temperature of smelting furnace controls at≤1050 DEG C, and melt temperature controls at≤770 DEG C, when melt is softening stay and change flat after, in stove, be evenly sprinkled into the 2# ground flux of 80kg, and stir metal in good time.
After furnace charge has all melted, when melt temperature reaches about 730 DEG C, add the Al-Be master alloy of 614kg Mg ingot and 8.5kg.Adition process and add rear 54kg2# ground flux cover, usage quantity is as the criterion to cover completely.Thoroughly should stir after adding, and temperature adjustment is stabilized in about 740 DEG C, after about spending 20 minutes, carry out stokehold sampling.
Sampling must be carried out at melt in the middle of fire door, carries out composition adjustment according to the control overflow in both analysis result and technique scheme.
After composition adjustment completes, adopt refining pipe to carry out argon gas refining in stove, refining time 20 minutes, refining temperature about 740 DEG C, during refining, bubble height should not more than 80mm.
Should leave standstill after refining completes, time of repose at least 25 minutes.
Adopt two rotors refinery by de-gassing device to carry out online degasification the melt after leaving standstill, refining gas consumption is 30L/min, and refining temperature is 720 ± 5 DEG C, and rotor speed is 300 ± 5rpm; Then adopt single-stage 30ppi ceramic filter plate to carry out on-line filtration, when changing screen plate, require the integrity of checked filter plate, and ensure to be in place, carefully put mass, and suitably toast; Then add Al-5Ti-B silk according to the amount of 1.5kg/t, carry out at line thinning.
After completing online treatment, cast by melt, casting temp is 735 DEG C, and when casting starts, having cast vehicle speed is 8mm/min, and cooling water flow is 10m
3/ h, after length to be cast reaches 300mm, by casting speed with the increasing amount adjustment of (1mm/min)/50mm to 14mm/min, by cooling water flow with (1m
3/ h) increasing amount adjustment of/50mm is to 20m
3/ h.
Cut off the water when gate part liquid still has when 1/3 during casting ending, stop when gate part will depart from crystallizer at once, forbid water droplet to gate part.
After having cast, carrying out homogenizing thermal treatment by casting the ingot blank obtained, with the Heating temperature of 495 DEG C heating, entering insulation after being heated to 465 DEG C, being incubated 32 hours, completing homogenizing thermal treatment.
Then anneal 8 hours at 360 DEG C, then carry out sawing accordingly to ingot casting, sawing gate part and bottom all about 350mm, obtains 7050 aluminium alloys.Casting rate is 90%.
The present invention carries out carrying out flaw detection according to technique scheme to 7050 aluminium alloys that the present invention obtains, 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 preparation technology of aviation alloyed aluminium provided by the invention can carry heavy alloyed ingot casting ratio of briquetting and flaw detection qualification rate.
The above is only the preferred embodiment of the present invention; it should be pointed out that for those skilled in the art, under the premise without departing from the principles of the invention; can also make some improvements and modifications, these improvements and modifications also should be considered as protection scope of the present invention.
Claims (10)
1. a preparation technology for aviation alloyed aluminium ingot casting, comprises the following steps:
A) carry out melting by after Cu source, Mg source, Zn source, Ti source, Zr source and the mixing of Al source, obtain melting thing;
B) by described steps A) the melting thing that obtains carries out online degasification, on-line filtration and at line thinning successively, obtains online treatment product;
C) by described step B) the online treatment product that obtains casts, and obtain aviation alloyed aluminium ingot blank, the speed of described casting is 8 ~ 14mm/min;
D) by described step C) the aviation alloyed aluminium ingot blank that obtains carries out homogenizing thermal treatment, obtains aviation alloyed aluminium ingot casting; Described aviation alloyed aluminium ingot casting comprises 7050 aluminium alloy cast ingots and 7A85 aluminium alloy cast ingot.
2. preparation technology according to claim 1, is characterized in that, described steps A) specifically comprise the following steps:
Carry out melting by after Cu source, Zn source, Ti source, Zr source and the mixing of Al source, after melt all melts, add the Be of Mg source and 0-0.0009%, carry out melting, obtain melting thing.
3. preparation technology according to claim 1, is characterized in that, the temperature of described melting is 800 ~ 1050 DEG C.
4. preparation technology according to claim 1, is characterized 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;
Describedly Al-5Ti-B silk is adopted to carry out at line thinning.
5. preparation technology according to claim 1, is characterized in that, the speed of described casting is 9 ~ 13mm/min.
6. preparation technology according to claim 1, is characterized in that, the temperature of described casting is 650 ~ 770 DEG C.
7. preparation technology according to claim 1, is characterized in that, in described casting, the flow of water coolant is 10 ~ 20m
3/ h.
8. preparation technology according to claim 1, is characterized in that, when the length of described casting is between 0mm ~ 300mm, in described castingprocesses, the flow of water coolant is 10 ~ 11m
3/ h;
As the length > 300mm of described casting, by the flow of water coolant in described castingprocesses with (1m
3/ h)/50mm speed increase, until the flow of described water coolant reaches 19 ~ 20m
3/ h.
9. preparation technology according to claim 1, is characterized in that, the heat treated holding temperature of described homogenizing is 460 ~ 470 DEG C;
The heat treated soaking time of described homogenizing is 30 ~ 35 hours.
10. the specification that preparation technology obtains as claimed in any one of claims 1 to 9 wherein is the aluminium alloy cast ingot of Φ 850mm.
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