CN106756675A - Aviation alloyed aluminium sheet material and its production method - Google Patents
Aviation alloyed aluminium sheet material and its production method Download PDFInfo
- Publication number
- CN106756675A CN106756675A CN201710194726.7A CN201710194726A CN106756675A CN 106756675 A CN106756675 A CN 106756675A CN 201710194726 A CN201710194726 A CN 201710194726A CN 106756675 A CN106756675 A CN 106756675A
- Authority
- CN
- China
- Prior art keywords
- aluminium
- sheet material
- production method
- aluminium alloy
- melt
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
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
- C22C1/00—Making non-ferrous alloys
- C22C1/02—Making non-ferrous alloys by melting
- C22C1/026—Alloys based on aluminium
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C1/00—Making non-ferrous alloys
- C22C1/02—Making non-ferrous alloys by melting
- C22C1/03—Making non-ferrous alloys by melting using master alloys
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C1/00—Making non-ferrous alloys
- C22C1/06—Making non-ferrous alloys with the use of special agents for refining or deoxidising
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)
- Metal Rolling (AREA)
Abstract
The invention provides a kind of aviation alloyed aluminium sheet material and its production method, it is related to aluminum alloy plate materials production field.The production method includes：To be stretched after aluminium alloy stock melting, casting, two-step homogenization treatment, hot rolling treatment, double_stage guide treatment；Wherein, two-step homogenization treatment includes：By aluminium alloy cast ingot with the programming rate of 10~40 DEG C/h, 460~470 DEG C are warming up to, are incubated 20~25h, be continuously heating to 475~480 DEG C, be incubated 6~8h, air cooling；Aluminium alloy stock includes by mass percentage：Solid aluminium material 25~35%, aluminium scrap material 40~50%, electrolyte 15~35%.The production method is conducive to being lifted the combination property of obtained aviation alloyed aluminium sheet material, makes its performance evenly, and intensity is bigger.In addition the aviation alloyed aluminium sheet material as obtained by the production method processing of above-mentioned aviation alloyed aluminium sheet material, its intensity is high, durability and damage tolerance strong, and combination property is good.
Description
Technical field
The present invention relates to aluminum alloy plate materials production field, in particular to a kind of aviation alloyed aluminium sheet material and its life
Product method.
Background technology
The combination property of 7150 aluminium alloys preferably, is suitable to for producing big specification slab and forging.It is large-scale with aircraft
Change and the material that anisotropy is small, performance uniformity is high is all the more made excessive demands in the integration of structural member.At present, manufacture large transport airplane and
The wing wallboard of passenger plane needs length up to the 7150-T7751 sheet alloys of more than 20m, but the performance of domestic sheet material is uneven.
Big aircraft main components are still needed import.
The content of the invention
It is an object of the invention to provide a kind of production method of aviation alloyed aluminium sheet material, by the improvement of technique with life
Output high intensity, durability and the strong aviation alloyed aluminium sheet material of damage tolerance.
Obtained another object of the present invention is to provide a kind of production method processing by above-mentioned aviation alloyed aluminium sheet material
Aviation alloyed aluminium sheet material, its intensity is high, durability and damage tolerance strong, and combination property is good.
What embodiments of the invention were realized in：
A kind of production method of aviation alloyed aluminium sheet material, it includes：Aluminium alloy stock is smelted into melt, melt is cast
Aluminium alloy cast ingot is formed, aluminium alloy cast ingot is stretched by after two-step homogenization treatment, hot rolling treatment, double_stage guide treatment；
Wherein, two-step homogenization treatment aluminium alloy cast ingot includes：By aluminium alloy cast ingot with the programming rate of 10~40 DEG C/h,
460~470 DEG C are warming up to, 20~25h is incubated, 475~480 DEG C are continuously heating to, 6~8h, air cooling is incubated；
Aluminium alloy stock includes by mass percentage：Solid aluminium material 25~35%, aluminium scrap material 40~50%, electrolyte 15
~35%.
A kind of aviation alloyed aluminium sheet material, it is obtained using the production method processing of above-mentioned aviation alloyed aluminium sheet material.
The aviation alloyed aluminium sheet material of the embodiment of the present invention and its beneficial effect of production method are：In the embodiment of the present invention
The Combined Treatment mode processed using two-step homogenization treatment and double_stage guide, can make the abundant solid solution of alloy product, and close
Second phase particles fully dissolve in gold, and indissoluble or insoluble particle form satiety and close solid solution with deformation streamline distribution, make alloy
Fracture toughness increases.Intensity by the obtained aviation alloyed aluminium sheet material of production method processing is high, and combination property is evenly, more
By force.
Brief description of the drawings
Technical scheme in order to illustrate more clearly the embodiments of the present invention, below will be attached to what is used needed for embodiment
Figure is briefly described, it will be appreciated that the following drawings illustrate only certain embodiments of the present invention, thus be not construed as it is right
The restriction of scope, for those of ordinary skill in the art, on the premise of not paying creative work, can also be according to this
A little accompanying drawings obtain other related accompanying drawings.
Fig. 1 is that the aviation alloyed aluminium sheet material that the embodiment of the present invention 2 is provided is 500nm's in resolution ratio after three-step aging
Under the conditions of institutional framework schematic diagram；
Fig. 2 is that the aviation alloyed aluminium sheet material that the embodiment of the present invention 2 is provided is 200nm's in resolution ratio after three-step aging
Under the conditions of institutional framework schematic diagram；
Fig. 3 be in comparative example of the present invention T6 states by after 120 DEG C/24h Ageing Treatments in resolution ratio under conditions of 0.5um
Tem observation result；
Fig. 4 be in comparative example of the present invention T6 states by after 120 DEG C/24h Ageing Treatments in resolution ratio under conditions of 0.2um
Tem observation result；
Fig. 5 be in comparative example of the present invention RRA states by resolution ratio being the condition of 50nm after 190 DEG C/20min Ageing Treatments
Under tem observation result；
Fig. 6 be in comparative example of the present invention RRA states by resolution ratio being the condition of 50nm after 190 DEG C/40min Ageing Treatments
Under tem observation result；
Fig. 7 be in comparative example of the present invention RRA states by resolution ratio being the condition of 50nm after 190 DEG C/60min Ageing Treatments
Under tem observation result；
Fig. 8 be in comparative example of the present invention RRA states by resolution ratio being the bar of 100nm after 190 DEG C/60min Ageing Treatments
Tem observation result under part；
Fig. 9 be comparative example of the present invention in T73 states by after 110 DEG C/8h+177 DEG C/8h Ageing Treatments resolution ratio be 50nm
Under conditions of tem observation result.
Specific embodiment
Embodiment of the present invention is described in detail below in conjunction with embodiment, but those skilled in the art will
Understand, the following example is merely to illustrate the present invention, and is not construed as limiting the scope of the present invention.It is unreceipted specific in embodiment
Condition person, the condition advised according to normal condition or manufacturer is carried out.Agents useful for same or the unreceipted production firm person of instrument, are
The conventional products that can be obtained by commercially available purchase.
A kind of production method of aviation alloyed aluminium sheet material, it includes：Aluminium alloy stock is smelted into melt, melt is cast
Aluminium alloy cast ingot is formed, aluminium alloy cast ingot is stretched by after two-step homogenization treatment, hot rolling treatment, double_stage guide treatment.
Specifically, step S1, melting includes：
Chemical composition and mass percent according to 7150 aluminium alloy standards prepare raw material, in 720 DEG C~760 DEG C of bar
Smelting aluminium alloy raw material under part, when aluminium alloy stock 50%~60% is molten into aluminium liquid, opens electromagnetic agitation, adds Zn ingots, oozes
Add thoroughly.After raw material of aluminum alloy all melts, add other compositions, and skimmed, adjusting component.
Wherein, aluminium alloy stock includes by mass percentage：Solid aluminium material 25~35%, aluminium scrap material 40~50%, electricity
Solution liquid 15~35%.
Solid aluminium material is the solid that composition is Al, specially aluminium ingot, and aluminium scrap material is the arm of angle material of identical alloying component, example
Such as：One or more in remelting aluminium ingot, ingot casting saw cutting head tailing, hot rolled plate crop tailing.
It should be noted that term " infiltration is added " represents and adds into melt Zn ingots that Zn ingots are not sunken to furnace bottom, also not
Float on surface, as infiltration is added.
Also included before casting step：Step S2 --- multistage purification treatment：
When multistage purification treatment is carried out to melt, S201 is first carried out：Gaseous mixture is refined.
By melt transfer to holding furnace, furnace side Ar and Cl are carried out2Gaseous mixture is refined, and composition is qualified and casting is made adequate preparation
Afterwards, melt stands appropriate time.
By to being blown into aluminum alloy melt not only insoluble in aluminum alloy melt and the inert gas that is not reacted with hydrogen, acquisition
Hydrogen-free bubble.Because these minute bubbles are in floating-upward process, Al on the one hand can be adsorbed2O3Deng field trash, on the other hand can also clamp
Pressure differential between nitrogen or argon gas bubbles and aluminium alloy contact surface, will be dissolved in the hydrogen suction bubble in aluminium alloy.Work as absorption
After the bubble floating of field trash and/or hydrogen is excluded to liquid level, the purpose of degassing and slagging-off can be reached.
Ar and Cl is used in the present embodiment2Gaseous mixture is refined, wherein, active gases chlorine does not dissolve in aluminum alloy melt,
But strong chemical reaction can occur with aluminium and the hydrogen being dissolved in aluminum alloy melt, generate HCl and AlCl insoluble in aluminum alloy melt3
Gas.These gases generated due to reaction and the Cl for not participating in reaction2This can play the work of adsorbed hydrogen and oxide inclusion
With so its refining effect ratio is far better using pure gas argon gas or argon gas.Typically terse treatment is carried out in logical chlorine
When, the temperature general control of aluminum alloy melt is at 690~720 DEG C, but the logical chlorine time is then different according to different alloy systems.
Although the effect of logical chlorine refining is preferably, complete equipment is more complicated, and chlorine is toxic, harmful and pair set
Standby, environment has in corrosiveness, therefore the present embodiment, by Cl2It is used in mixed way with Ar, compared with logical chlorine is refined, leads to gaseous mixture
The refining time of body refining saves half, and due to having used argon gas, alleviates chlorine to human body and the corrosiveness of equipment,
So that condition of work is also greatly improved.
After gaseous mixture refining terminates, then carry out S202：Degasification removal of impurities.
Degasification removal of impurities：Under the conditions of 700 DEG C~730 DEG C of melt temperature, melt is carried out into melt through SNIF degassing apparatus and is removed
Gas；Then the foamed ceramic panel of 30PPI and 50PPI is separately heated to 600~750 DEG C, make melt sequentially pass through 30PPI and
The foamed ceramic panel of 50PPI carries out melt filtration.
The melt that the present embodiment is provided first passes through Ar and Cl2Gaseous mixture is refined, can remove gas in melt and
Impurity, further recycles SNIF degassing apparatus to carry out melt degasification, and the foamed ceramic panel of 30PPI and 50PPI is melted
Body is filtered so that the air content and impurity content of melt are further reduced, while after foamed ceramic panel heating, can effectively prevent bubble
Foam ceramic wafer is blocked, and effectively removal melt field trash.Additionally, according to the principle of slag gas association, while field trash is removed,
Hydrogen in melt also can further decline.By removal of impurities degasification twice, the gassiness and impurity content in melt are significantly reduced, be
The homogeneous aluminium alloy cast ingot of the clean fine and smooth, color and luster of casting surface is laid a good foundation.
After degasification removal of impurities, multistage purification treatment also includes S203：Crystal grain refinement.
Alterant is added toward melt, melt is 100 with the mass ratio of alterant：0.01~0.03.Add alterant energy
Enough improve crystallization process, preferably by Al5Ti1B crystal grain refinements silk as alterant.
Cleaning molten uses multi-stage combination cleaning molten technology, ingot metallurgy quality is reached the level of High Purity, makes casting
Ingot metallurgy quality meets：1 grade of grain size；[H]≤0.1ml/100gAl；Na ＜ 2PPm；Ca ＜ 4PPm；Slag ＜ 50K/kg.Product
Forming property and mechanical property it is more excellent.Melt hydrogen content after being processed in line is few, impurity content is reduced, while making
Aluminium alloy cast ingot evenly, it is tiny.Certainly, in other embodiments, also can be using purification technique of the prior art to melt
Purified.
Step S3, casting：By melt cast into aluminium alloy cast ingot (480 × 1560 × Lmm).
Step S4, two-step homogenization treatment：By aluminium alloy cast ingot with the programming rate of 10~40 DEG C/h, it is warming up to 460~
470 DEG C, 20~25h is incubated, is continuously heating to 475~480 DEG C, be incubated 6~8h, air cooling of coming out of the stove.
In the present embodiment, Homogenization Treatments are different from Homogenization Treatments of the prior art, and twin-stage is used in the present embodiment
Homogenization Treatments, that is to say and operated by a heating and heat preservation, then be operated by once continuing heating and heat preservation, in different high temperature bars
Held for some time under part, is conducive to improving the uniformity coefficient of ingot casting, is conducive to improving the plasticity of ingot casting, reduces resistance of deformation,
Be conducive to the fabricated product of ingot casting or the end-use properties of casting.For example：Corrosion resistance is improved, lamellar tissue is prevented, weakens material
Material anisotropic, raising structure stability, prevent creep from causing material shape size to change etc..Two-step homogenization treatment can make
Second phase particles in alloy fully dissolve, and indissoluble or insoluble particle form satiety and close solid solution with deformation streamline distribution, make conjunction
The fracture toughness of gold increases.
Also included before hot rolling treatment step：Step S5, milling face：
The expanding end of aluminium alloy cast ingot and gate end sawing are fallen, ingot casting upper and lower surface and two sides are carried out into milling face；Milling
The surface that face can enable aluminum alloy to ingot casting is more smooth, and then lifts the quality of aluminium alloy cast ingot.
Step S6, hot rolling treatment：Aluminium alloy cast ingot is heated to 400~450 DEG C, 1~3h is incubated, thickness is then hot-rolled down to
12-150mm aluminium alloy thick plates, finishing temperature is 320 DEG C.
In the present embodiment, hot rolling treatment is carried out on (1+5) formula hot continuous rolling production line, wherein, " (1+5) Shi Relian
Roll " represent, hot-rolling mill and 5 hot-rolling mills of 3000mm that aluminium alloy cast ingot is placed in 1 4100mm are combined into rolling.
Step S7, double_stage guide treatment：By the aluminium alloy cast ingot after hot rolling at 460~470 DEG C, 0.5~3h is incubated, after
It is continuous to be warming up to 475~478 DEG C, 0.5~2h is incubated, water-cooled is carried out immediately.
Aluminium alloy cast ingot after hot rolling is aluminium alloy thick plate, and by aluminium alloy thick plate, progressively intensification solution treatment can make most
Whole solid solubility temperature exceedes polyphase eutectic temperature without producing burnt structure, so as to improve solid solution degree and the conjunction of remaining solvable crystallization
Golden mechanical property.By heating and thermal insulation, make solvable phased soln, then chilling, a large amount of hardening constituents is solid-solubilized in αsolidsolution, obtain
Supersaturated solid solution is obtained, for the hardness, intensity and the corrosion stability that improve alloy are prepared.
The organizational controls of alloy is extremely important in alloy solid solution processing procedure, rising and solution time with solid solubility temperature
Extension, the increase of precipitated phase dissolution degree, but the crystal grain of alloy is grown up simultaneously, and recrystallization degree is improved, and alloy can be caused again
Combination property declines.7150 alloys are important Aircraft Structure Materials, the present embodiment by changing solid solution treatment process, systematically
Influence of the research solid solution treatment process to the microscopic structure and mechanical property of 7150 alloys, it is intended to consolidate to formulate 7150 alloy novels
Molten aging strengthening model provides test basis.
Step S8, stretching：Aluminium alloy thick plate after double_stage guide is processed carries out 1.8 on 80MN jaw type stretching-machines~
2.1% predeformation.
After stretching step, also including step S9, three-step aging
First order timeliness：121 DEG C are warming up to, 23~25h is incubated,
Second level timeliness：180~190 DEG C are continuously heating to, 20min~1.5h is incubated；And
Third level timeliness：Then in 121 DEG C, it is incubated 23~25h.
Specifically, the space of common aging furnace is controlled to specified altitude assignment with lower baffle plate (highly depending on thickness of slab).Will
Aluminium alloy thick plate after stretching adds aging furnace, presses：121 DEG C/23~25h+180~190 DEG C/20min~1.5h+121 DEG C/23
The institution of prescription of~25h is implemented.Wherein, the follow-up temperature of continuing rising of first order timeliness carries out second level timeliness, and after the timeliness of the second level, no
121 DEG C can be cooled to, third level timeliness is carried out.Can be after the timeliness of the second level, fast cooling to room temperature is then warming up to again
121 DEG C, carry out third level timeliness.In the present embodiment, preferably first order timeliness is complete is directly warmed up to 180~190 DEG C from 121 DEG C,
1~5 DEG C/min of programming rate.Room temperature, 10~20 DEG C/min of cooling velocity are cooled fast to after the timeliness of the second level.The 3rd is carried out again
Level timeliness.
It should be noted that heated up using heating rate (1~5 DEG C/min) faster in the embodiment of the present invention, energy
Ensure first order timeliness to the recurrence timeliness of second level timeliness, by the 1st grade of transgranular particle back dissolving of Precipitation to solid solution,
The particle of crystal boundary is roughened, discontinuous recipittaion, so as to improve alloy corrosion.Simultaneously with cooldown rate (10 faster
~20 DEG C/min) to be lowered the temperature, it is to avoid overlong time causes the supersaturated solid solution for decomposing to reconfigure, and further lifts alloy
Combination property.
The production method of above-mentioned aviation alloyed aluminium sheet material, is purified to melt by multistage purification treatment and (is mixed
Gas refining, degasification removal of impurities and crystal grain refinement), the gas in melt, slag inclusion are discharged, purer melt is obtained, make ingot casting smelting
Golden amount meets：1 grade of grain size；[H]≤0.1ml/100gAl；Na ＜ 2PPm；Ca ＜ 4PPm；Slag ＜ 25K/kg.Make ingot casting smelting
Golden amount reaches the level of High Purity, and the forming property and mechanical property of product are more excellent.
Meanwhile, using two-step homogenization treatment and the Combined Treatment mode of double_stage guide treatment in the embodiment of the present invention,
The abundant solid solution of alloy product, and second phase particles in alloy can be made fully to dissolve, indissoluble or insoluble particle are with flow lines point
Cloth, forms satiety and closes solid solution, and making the fracture toughness of alloy increases.Also, the temperature and double_stage guide of two-step homogenization treatment
The temperature for the treatment of is identical, makes the combination property of alloy evenly.
Additionally, using three-step aging stove, non-generic stove is realized.Three-step aging stove is on the basis of common aging furnace, to subtract
Few physics timeliness space, increases secondary time effect intensification intensity and intensity of cooling (1~5 DEG C/min of heating rate；Cooling velocity 10~
20 DEG C/min), replace import, with wide market prospects and significant economic benefit.
Further illustrated below in conjunction with specific embodiment.
Embodiment 1
A kind of production method of aviation alloyed aluminium sheet material is present embodiments provided, it is comprised the following steps：
Melting：Chemical composition and mass percent according to 7150 aluminium alloy standards prepare raw material, wherein, aluminium alloy is former
Material includes by mass percentage：Solid aluminium material 25%, aluminium scrap material 40%, electrolyte 35%.The melting under conditions of 720 DEG C DEG C
Aluminium alloy stock, when aluminium alloy stock 50%% is molten into aluminium liquid, opens electromagnetic agitation, adds Zn ingots, and infiltration is added.When aluminium is closed
Golden raw material are all after fusing, add other compositions, and skimmed, adjusting component.
Casting：By melt cast into aluminium alloy cast ingot (480 × 1560 × 8650mm).
Two-step homogenization treatment：By aluminium alloy cast ingot with the programming rate of 30 DEG C/h, 460 DEG C are warming up to, are incubated 25h, after
It is continuous to be warming up to 475 DEG C, it is incubated 8h, air cooling of coming out of the stove.
Milling face：The expanding end of aluminium alloy cast ingot and gate end sawing are fallen, ingot casting upper and lower surface and two sides are carried out into milling
Face；The surface that milling face can enable aluminum alloy to ingot casting is more smooth, and then lifts the quality of aluminium alloy cast ingot.
Hot rolling treatment：Aluminium alloy cast ingot is heated to 400 DEG C, 3h is incubated, thickness 12mm aluminium alloy thick plates are then hot-rolled down to,
Finishing temperature is 320 DEG C.
Double_stage guide treatment：By the aluminium alloy cast ingot after hot rolling at 460 DEG C, 3h is incubated, is continuously heating to 475 DEG C, protected
Warm 2h, carries out water-cooled immediately.
Stretching：Aluminium alloy thick plate after double_stage guide is processed carries out 1.8% predeformation on 80MN jaw type stretching-machines.
Embodiment 2
A kind of production method of aviation alloyed aluminium sheet material is present embodiments provided, it is comprised the following steps：
Melting：Chemical composition and mass percent according to 7150 aluminium alloy standards prepare raw material, wherein, aluminium alloy is former
Material includes by mass percentage：Solid aluminium material 35%, aluminium scrap material 50%, electrolyte 15%.The smelting aluminum under conditions of 760 DEG C
Alloy raw material, when aluminium alloy stock 60% is molten into aluminium liquid, opens electromagnetic agitation, adds Zn ingots, and infiltration is added.When aluminium alloy is former
Material all after fusing, adds other compositions, and skimmed, adjusting component.
Casting：By melt cast into aluminium alloy cast ingot (480 × 1560 × 8650mm).
Two-step homogenization treatment：By aluminium alloy cast ingot with the programming rate of 38 DEG C/h, 470 DEG C are warming up to, are incubated 20h, after
It is continuous to be warming up to 480 DEG C, it is incubated 6h, air cooling of coming out of the stove.
Milling face：The expanding end of aluminium alloy cast ingot and gate end sawing are fallen, ingot casting upper and lower surface and two sides are carried out into milling
Face；The surface that milling face can enable aluminum alloy to ingot casting is more smooth, and then lifts the quality of aluminium alloy cast ingot.
Hot rolling treatment：Aluminium alloy cast ingot is heated to 450 DEG C, 1h is incubated, thickness 150mm aluminium alloys is then hot-rolled down to thick
Plate, finishing temperature is 320 DEG C.
Double_stage guide treatment：By the aluminium alloy cast ingot after hot rolling at 470 DEG C, 0.5h is incubated, is continuously heating to 478 DEG C,
Insulation 0.5h, carries out water-cooled immediately.
Stretching：Aluminium alloy thick plate after double_stage guide is processed carries out 2.1% predeformation on 80MN jaw type stretching-machines.
Three-step aging：121 DEG C are warming up to, 23h is incubated, 180 DEG C, insulation are continuously heating to the programming rate of 1 DEG C/min
1.5h；Then with the cooling velocity fast cooling of 10 DEG C/min to room temperature, 121 DEG C are then warming up to again, are incubated 23h, obtain final product this
The aviation alloyed aluminium sheet material provided in embodiment, detects to the aviation alloyed aluminium sheet material in the present embodiment, its tissue
Structure can be found in Fig. 1 and Fig. 2.As can be seen from Figure 1：The transgranular hardening constituent by uniform small and dispersed shape of T6 states (peak value) alloy
Composition, electron diffraction analysis shows hardening constituent for η ' Xiang He GP areas mixture, so the intensity of alloy is very high.Additionally, also considerable
The Al3Zr particles of a large amount of disperses are observed, plays a part of thinning microstructure, it is high to the intensity of alloy also to contribute.Most of crystal boundary
On precipitated phase it is continuously distributed along crystal boundary, crystal boundary is not obvious without Precipitation band (PFZ).So, the corrosion resistance of alloy is low.
Embodiment 3
A kind of production method of aviation alloyed aluminium sheet material is present embodiments provided, it is comprised the following steps：
Melting：Chemical composition and mass percent according to 7150 aluminium alloy standards prepare raw material, wherein, aluminium alloy is former
Material includes by mass percentage：Solid aluminium material 30%, aluminium scrap material 45%, electrolyte 25%.The smelting aluminum under conditions of 740 DEG C
Alloy raw material, when aluminium alloy stock 55% is molten into aluminium liquid, opens electromagnetic agitation, adds Zn ingots, and infiltration is added.When aluminium alloy is former
Material all after fusing, adds other compositions, and skimmed, adjusting component.
Multistage purification treatment：By melt transfer to holding furnace, furnace side Ar and Cl are carried out2Gaseous mixture is refined, and melt is passed through
SNIF degassing apparatus carries out melt degasification；Then the foamed ceramic panel of 30PPI and 50PPI is separately heated to 600 DEG C, makes melt
The foamed ceramic panel for sequentially passing through 30PPI and 50PPI carries out melt filtration.After degasification removal of impurities, added in toward melt rotten
Agent, melt is 100 with the mass ratio of alterant：0.01 carries out crystal grain refinement treatment, after the completion for the treatment of.
Casting：By melt cast into aluminium alloy cast ingot (480 × 1560 × 8650mm).
Two-step homogenization treatment：By aluminium alloy cast ingot with the programming rate of 10 DEG C/h, 465 DEG C are warming up to, are incubated 22h, after
It is continuous to be warming up to 478 DEG C, it is incubated 7h, air cooling of coming out of the stove.
Milling face：The expanding end of aluminium alloy cast ingot and gate end sawing are fallen, ingot casting upper and lower surface and two sides are carried out into milling
Face；The surface that milling face can enable aluminum alloy to ingot casting is more smooth, and then lifts the quality of aluminium alloy cast ingot.
Hot rolling treatment：Aluminium alloy cast ingot is heated to 430 DEG C, 2h is incubated, thickness 120mm aluminium alloys is then hot-rolled down to thick
Plate, finishing temperature is 320 DEG C.
Double_stage guide treatment：By the aluminium alloy cast ingot after hot rolling at 465 DEG C, 2h is incubated, is continuously heating to 477 DEG C, protected
Warm 1h, carries out water-cooled immediately.
Stretching：Aluminium alloy thick plate after double_stage guide is processed carries out 2% predeformation on 80MN jaw type stretching-machines.
Three-step aging：121 DEG C are warming up to, 24h is incubated, 190 DEG C, insulation are continuously heating to the programming rate of 5 DEG C/min
20min；Then with 20 DEG C/min cooling velocities fast cooling to room temperature, 121 DEG C are warming up to again, be incubated 25h.Obtain this implementation
The aviation alloyed aluminium sheet material provided in example, detects that testing result is such as to the aviation alloyed aluminium sheet material in the present embodiment
Under：RRA temper alloys intergranular structure is similar to T6 states, by a large amount of tiny, disperse precipitation strength phase compositions, electronic diffraction point
Analysis shows hardening constituent predominantly η ' and η phases, therefore, the intensity of alloy is very high；And Grain Boundary Precipitates return state more than corresponding
Plus discontinuous and roughening, the structure is conducive to improving the resistance to corrosion of alloy.
Embodiment 4
A kind of production method of aviation alloyed aluminium sheet material is present embodiments provided, it is comprised the following steps：
Melting：Chemical composition and mass percent according to 7150 aluminium alloy standards prepare raw material, wherein, aluminium alloy is former
Material includes by mass percentage：Solid aluminium material 32%, aluminium scrap material 48%, electrolyte 20%.The smelting aluminum under conditions of 750 DEG C
Alloy raw material, when aluminium alloy stock 58% is molten into aluminium liquid, opens electromagnetic agitation, adds Zn ingots, and infiltration is added.When aluminium alloy is former
Material all after fusing, adds other compositions, and skimmed, adjusting component.
Multistage purification treatment：By melt transfer to holding furnace, furnace side Ar and Cl are carried out2Gaseous mixture is refined, and melt is passed through
SNIF degassing apparatus carries out melt degasification；Then the foamed ceramic panel of 30PPI and 50PPI is separately heated to 750 DEG C, makes melt
The foamed ceramic panel for sequentially passing through 30PPI and 50PPI carries out melt filtration.After degasification removal of impurities, added in toward melt rotten
Agent, melt is 100 with the mass ratio of alterant：0.03 carries out crystal grain refinement treatment, after the completion for the treatment of.
Casting：By melt cast into aluminium alloy cast ingot (480 × 1560 × 8650mm).
Two-step homogenization treatment：By aluminium alloy cast ingot with the programming rate of 20 DEG C/h, 466 DEG C are warming up to, are incubated 24h, after
It is continuous to be warming up to 479 DEG C, it is incubated 6h, air cooling of coming out of the stove.
Milling face：The expanding end of aluminium alloy cast ingot and gate end sawing are fallen, ingot casting upper and lower surface and two sides are carried out into milling
Face；The surface that milling face can enable aluminum alloy to ingot casting is more smooth, and then lifts the quality of aluminium alloy cast ingot.
Hot rolling treatment：Aluminium alloy cast ingot is heated to 443 DEG C, 3h is incubated, thickness 20mm aluminium alloy thick plates are then hot-rolled down to,
Finishing temperature is 320 DEG C.
Double_stage guide treatment：By the aluminium alloy cast ingot after hot rolling at 463 DEG C, 1h is incubated, is continuously heating to 476 DEG C, protected
Warm 1h, carries out water-cooled immediately.
Stretching：Aluminium alloy thick plate after double_stage guide is processed carries out 1.9% predeformation on 80MN jaw type stretching-machines.
Three-step aging：121 DEG C are warming up to, 24h is incubated, 190 DEG C, insulation are continuously heating to the programming rate of 5 DEG C/min
20-70min；Then with 20 DEG C/min cooling velocities fast cooling to room temperature, 121 DEG C are warming up to again, be incubated 25h.Obtain this
The aviation alloyed aluminium sheet material provided in embodiment, detects to the aviation alloyed aluminium sheet material in the present embodiment, detection knot
Fruit is as follows：RRA temper alloys intergranular structure is similar to T6 states, and by a large amount of tiny, disperse precipitation strength phase compositions, electronics spreads out
Analysis shows hardening constituent predominantly η ' and η phases are penetrated, therefore, the intensity of alloy is very high；And Grain Boundary Precipitates return state than corresponding
More discontinuous and roughening, the structure is conducive to improving the resistance to corrosion of alloy.
Comparative example
Firstth, the performance detection of the aviation alloyed aluminium sheet material of the present embodiment
Aviation alloyed aluminium sheet material and country's mark under the aviation alloyed aluminium sheet material, the T6 states that provide embodiment 4
The performance of the aviation alloyed aluminium sheet material of quasi- index is detected that detection structure is referring to table 1.
The performance detection contrast of the different aviation alloyed aluminium sheet materials of table 1.
As can be seen from Table 1, the intensity and elongation percentage of embodiment 4 are higher than T6 state, and Peeling Corrosion is higher than T6.
Secondth, performance impact of the Homogenization Treatments to aviation alloyed aluminium sheet material
In the parameter Selection experiment of Homogenization Treatments, the chemical constituent content in comparative example 1~3 is same as Example 4,
And production method is roughly the same with embodiment 4, its difference be the Homogenization Treatments step in production method has been carried out it is right
Than experiment.Concrete outcome refers to table 2：
The parameter Selection experiment result of the Homogenization Treatments of table 2.
Aluminium alloy cast ingot without Homogenization Treatments has serious microstructure segregation, and alloy is equal through 476 DEG C × 24h monopoles
After homogenizing treatment, the non-equilibrium phase on crystal boundary has been reduced, and has formed discontinuously arranged, and component segregation is improved；Extension is single
After the time of level Homogenization Treatments (476 DEG C × 30h), the change of its crystal boundary effect is not notable.Increase on the basis of monopole homogenization
The later stage heating and heat preservation of 479 DEG C × 6h, uniformization effect is more preferable, the dissolving increasing number of non-equilibrium phase, and crystal boundary is more straight, and
Shape is regular, and ingot casting intensity is big, and rigidity is strong, eliminates the nonequilibrium freezing eutectic structure on ingot casting crystal boundary, and crystal boundary is in linear,
After Ageing Treatment, its mechanical property is more excellent.
3rd, performance impact of the solution treatment to aviation alloyed aluminium sheet material
In experiment of the solution treatment to the performance impact of aviation alloyed aluminium sheet material, the chemical constituent in comparative example 4~7
Content is same as Example 4, and production method is roughly the same with embodiment 4, and its difference is to the solid solution in production method
Handling process has carried out contrast test.Concrete outcome refers to table 3：
The solution treatment of table 3. is contrasted to the performance impact of aviation alloyed aluminium sheet material
During solution treatment, the diffusion velocity of Mg is very fast with respect to Cu, makes Al2CuMg phases gradually think rich Cu conversions,
When burning occur in 480 DEG C of solution treatment, tensile strength, the yield strength of alloy are not substantially reduced alloy, but in order to ensure
Alloy has excellent combination property, and burning should be avoided the occurrence of during alloy solid solution.
In the embodiment of the present invention, from 460~470 DEG C, 0.5~3h is incubated, is continuously heating to 475~478 DEG C, insulation
0.5~2h, carries out the solid solution system of water-cooled immediately, and solid solution is first carried out at a temperature of less than 475 DEG C, then it is warming up to 475~
478 DEG C, second solid solution is carried out, be divided into solid solution twice rather than carry out solid solution at 475 DEG C of single temperature, be conducive to lifting to close
The tensile strength and yield strength of gold, so as to improve the combination property of alloy.
4th, performance impact of the Ageing Treatment to aviation alloyed aluminium sheet material
3 kinds of tensile strength (R of institution of prescription are listed successivelym/ MPa), yield strength (Rp0.2/ MPa), elongation
Loss (Rm loss/%) electrical conductivity [λ/(MS/m)] and total effect time (t/h) of (δ/%), tensile strength relative to T6 states.Tool
Body situation refers to table 4：
Performance impact contrast of the different institutions of prescription of table 4. to aviation alloyed aluminium sheet material
The tem observation result of embodiment 4 refers to Fig. 5, Fig. 6, Fig. 7 and Fig. 8, and the tem observation result of comparative example 8 is referred to
Fig. 3~Fig. 4：The tem observation result of comparative example 9 refers to Fig. 9：RRA temper alloys intergranular structure is similar to T6 states, by a large amount of
Tiny, disperse precipitation strength phase composition, electron diffraction analysis shows hardening constituent predominantly η ' and η phases, therefore, alloy it is strong
Degree is very high；And Grain Boundary Precipitates are more more discontinuous than corresponding recurrence state and are roughened, the structure is conducive to improving the anti-corruption of alloy
Erosion ability.In three kinds of institutions of prescription, the tensile strength highest of single-stage peak timeliness, but electrical conductivity is only 17.7MS/m.Twin-stage mistake
Institution of prescription, conductivity value reaches 22.0MS/m, but its tensile strength loss about 9%, using 121 DEG C/24h+190 DEG C/20min
During the three-level Wetted constructures technique of+121 DEG C/25h, the tensile strength loss about 5% of alloy, electrical conductivity has reached 21.8MS/
m；The electrical conductivity of its electrical conductivity and twin-stage overaging is being kept in the case of same level, the loss of its tensile strength is significantly lower than
The tensile strength loss of twin-stage Wetted constructures alloy, total timeliness of three-level Wetted constructures is suitable with twin-stage overaging, has
More preferable combination property is obtained beneficial to alloy.
5th, performance impact of the Ageing Treatment parameter to aviation alloyed aluminium sheet material
Comparative example 10-a and comparative example 10-b is used in identical institution of prescription, but comparative example 1-a, in second level timeliness
Afterwards, third level timeliness is carried out by the way of being cooled to 121 DEG C；And in comparative example 10-b, after the timeliness of the second level, using quick
Room temperature is cooled to, then third level timeliness is carried out by the mode of room temperature to 121 DEG C.Comparative example 10-a and comparative example are detected successively
Tensile strength (the R of 10-bm/ MPa), yield strength (Rp0.2/ MPa), elongation (δ/%), tensile strength relative to T6 states damage
Lose (Rm loss/%) electrical conductivity [λ/(MS/m)] and total effect time (t/h).Concrete condition refers to table 5：
Performance impact contrast of the different timeliness parameters of table 5. to aviation alloyed aluminium sheet material
As can be seen from the above table, take the high temperature fast cooling by second level timeliness to room temperature, 121 are then warming up to again
DEG C third level timeliness is carried out, it is compared to being directly cooled to for temperature needed for third level timeliness, and tensile strength, yield strength are equal
It has been lifted that, while tensile strength loss is reduced, using the institution of prescription of comparative example 10-b, the combination property of alloy is more excellent.Just
Embody the true meaning of retrogression heat treatment.
Additionally, in the present embodiment, first order timeliness be warming up to second level timeliness using 1~5 DEG C of specific heating rate/
Min, further, second level timeliness is cooled to room temperature, using 10~20 DEG C/min of specific rate of temperature fall, realizes fast prompt drop
Temperature, advantageously reduces the density of matrix precipitate.
6th, the selection of technique is purified
In the Selection experiment of purification technique, the chemical constituent content in comparative example 11~16 is same as Example 4, and
Production method is roughly the same with embodiment 4, and its difference is to have carried out contrast test to the purification technique in production method.Specifically
Result refers to table 6：
Table 6. purifies the choice experiment result of technique
Requirement to aluminium alloy melt degree of purity, the difference for being typically due to kind and purposes has certain difference.Generally
Hydrogen content requirement is less than 0.2ml/100gAl, but should be in below 0.1ml/100gAl for the aeronautical material of particular/special requirement.Sodium contains
Amount should be in below 5ppm；Non-metallic inclusion is not allow for the particle and aggregation of 1~5Lm sizes, inclusion content it is more low more
It is good.And grain size is measuring for grain size.Combined by upper table, in the present embodiment and use multistage purification technique, make to melt
The hydrogen content and impurity content of body are greatly lowered, while grain size meets 1 grade of requirement.
Embodiments described above is a part of embodiment of the invention, rather than whole embodiments.Reality of the invention
The detailed description for applying example is not intended to limit the scope of claimed invention, but is merely representative of selected implementation of the invention
Example.Based on the embodiment in the present invention, what those of ordinary skill in the art were obtained under the premise of creative work is not made
Every other embodiment, belongs to the scope of protection of the invention.
Claims (10)
1. a kind of production method of aviation alloyed aluminium sheet material, it is characterised in that it includes：Aluminium alloy stock is smelted into molten
Body, casts the melt composition aluminium alloy cast ingot, and the aluminium alloy cast ingot is by two-step homogenization treatment, hot rolling treatment, twin-stage
Stretched after solution treatment；
Wherein, two-step homogenization processes the aluminium alloy cast ingot and includes：By the aluminium alloy cast ingot with the intensification of 10~40 DEG C/h
Speed, is warming up to 460~470 DEG C, is incubated 20~25h, is continuously heating to 475~480 DEG C, is incubated 6~8h, air cooling；
The aluminium alloy stock includes by mass percentage：Solid aluminium material 25~35%, aluminium scrap material 40~50%, electrolyte 15
~35%.
2. the production method of aviation alloyed aluminium sheet material according to claim 1, it is characterised in that double_stage guide processes institute
Stating aluminium alloy cast ingot includes：The aluminium alloy cast ingot after by hot rolling is incubated 0.5~3h at 460~470 DEG C, continues to heat up
To 475~478 DEG C, 0.5~2h is incubated, water-cooled is carried out immediately.
3. the production method of aviation alloyed aluminium sheet material according to claim 1, it is characterised in that closed the aluminium is stretched
After golden plate material, also including carrying out three-step aging treatment to the aluminum alloy plate materials：
First order timeliness：121 DEG C are warming up to, 23~25h is incubated,
Second level timeliness：180~190 DEG C are continuously heating to, 20min~1.5h is incubated；And
Third level timeliness：Then in 121 DEG C, it is incubated 23~25h.
4. the production method of aviation alloyed aluminium sheet material according to claim 3, it is characterised in that in the first order
Programming rate after effect is 1~5 DEG C/min.
5. the production method of aviation alloyed aluminium sheet material according to claim 3, it is characterised in that at the second level
After effect, after being cooled to room temperature, then heat up and carry out the third level timeliness.
6. the production method of aviation alloyed aluminium sheet material according to claim 5, it is characterised in that the second level timeliness
Cooling velocity afterwards is 10~20 DEG C/min.
7. the production method of aviation alloyed aluminium sheet material according to claim 1, it is characterised in that draw high the aluminium alloy
The tensile deformation amount of ingot casting is 1.9%~2.1%.
8. the production method of aviation alloyed aluminium sheet material according to claim 1, it is characterised in that aluminium described in hot rolling treatment
Alloy cast ingot includes：The aluminium alloy cast ingot is heated to 400~450 DEG C, 1~3h is incubated, hot continuous rolling to thickness is 12-
The aluminium alloy plate of 150mm, finishing temperature is 320 DEG C.
9. the production method of the aviation alloyed aluminium sheet material according to any one of claim 1~8, it is characterised in that molten
It is described also including carrying out multistage purification treatment to the melt before the melt is cast after refining the aluminium alloy stock
Multistage purification treatment includes：
Gaseous mixture is refined：The melt is gone to and carried out in holding furnace furnace side Ar and Cl2Gaseous mixture is refined；
Degasification removal of impurities：The melt is carried out into melt degasification through SNIF degassing apparatus；Then the foam of 30PPI and 50PPI is made pottery
Porcelain plate is separately heated to 600~750 DEG C, makes that the melt sequentially passes through the 30PPI and the foamed ceramic panel of 50PPI is melted
Body is filtered；And
Crystal grain refinement：Alterant is added toward the melt, the melt is 100 with the mass ratio of the alterant：0.01~
0.03。
10. a kind of aviation alloyed aluminium sheet material, it is characterised in that it is using the aviation as described in any one of claim 1~9
Processed with the production method of aluminum alloy plate materials and obtained.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710194726.7A CN106756675B (en) | 2017-03-28 | 2017-03-28 | Aviation alloyed aluminium plate and its production method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710194726.7A CN106756675B (en) | 2017-03-28 | 2017-03-28 | Aviation alloyed aluminium plate and its production method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106756675A true CN106756675A (en) | 2017-05-31 |
| CN106756675B CN106756675B (en) | 2019-01-18 |
Family
ID=58966530
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710194726.7A Active CN106756675B (en) | 2017-03-28 | 2017-03-28 | Aviation alloyed aluminium plate and its production method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106756675B (en) |
Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107267898A (en) * | 2017-07-07 | 2017-10-20 | 哈尔滨中飞新技术股份有限公司 | A kind of 7075 aluminium alloy homogenising treatment methods |
| CN107723634A (en) * | 2017-10-24 | 2018-02-23 | 山东南山铝业股份有限公司 | Realize the heat treatment method and aviation alloyed aluminium sheet material of T77 three-step agings |
| CN107740013A (en) * | 2017-10-24 | 2018-02-27 | 山东南山铝业股份有限公司 | The three-step aging heat treatment method of aviation alloyed aluminium, the production method and aluminum alloy plate materials of aviation alloyed aluminium sheet material |
| CN109055875A (en) * | 2018-10-27 | 2018-12-21 | 安徽创弘精密机械有限公司 | A kind of heat treatment process improving aluminium alloy extrusions intensity |
| CN110172653A (en) * | 2019-01-31 | 2019-08-27 | 苏州铭恒金属科技有限公司 | It is a kind of improve aluminium alloy cast ingot conductivity homogenizing method and the aluminium alloy cast ingot as made from the homogenizing method |
| CN111424197A (en) * | 2020-04-14 | 2020-07-17 | 广西南南铝加工有限公司 | Corrosion-resistant aluminum alloy for aviation and preparation method thereof |
| CN111455239A (en) * | 2020-04-14 | 2020-07-28 | 广西南南铝加工有限公司 | Ultrahigh-strength aviation aluminum alloy and preparation method thereof |
| CN111702009A (en) * | 2020-06-28 | 2020-09-25 | 山东南山铝业股份有限公司 | Preparation method of T4 or T42-state 2024 aluminum alloy coated aluminum sheet |
| CN111876702A (en) * | 2020-08-06 | 2020-11-03 | 西南铝业（集团）有限责任公司 | Solution quenching heat treatment process for industrially producing 7150 alloy thick plate |
| CN111926226A (en) * | 2020-08-12 | 2020-11-13 | 烟台南山学院 | High-strength plastic aluminum alloy and preparation method thereof |
| CN112553550A (en) * | 2020-11-23 | 2021-03-26 | 天津忠旺铝业有限公司 | Production process of 7-series aluminum alloy thick plate with high damage tolerance and low quenching sensitivity |
| CN115491618A (en) * | 2022-09-23 | 2022-12-20 | 湖南中创空天新材料股份有限公司 | Aging heat treatment system for reducing anisotropy of aluminum alloy ring piece and improving comprehensive performance |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103898382A (en) * | 2014-03-27 | 2014-07-02 | 北京科技大学 | Ultra-strength and high-toughness corrosion resistant Al-Zn-Mg-Cu aluminum alloy material and preparation method thereof |
| CN105821354A (en) * | 2016-04-20 | 2016-08-03 | 中南大学 | Method for improving size stability of aluminum alloy for aerospace |
-
2017
- 2017-03-28 CN CN201710194726.7A patent/CN106756675B/en active Active
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103898382A (en) * | 2014-03-27 | 2014-07-02 | 北京科技大学 | Ultra-strength and high-toughness corrosion resistant Al-Zn-Mg-Cu aluminum alloy material and preparation method thereof |
| CN105821354A (en) * | 2016-04-20 | 2016-08-03 | 中南大学 | Method for improving size stability of aluminum alloy for aerospace |
Non-Patent Citations (3)
| Title |
|---|
| 刘文军等: "均匀化对7050铝合金板材淬火敏感性的影响", 《中国有色金属学报》 * |
| 李念奎等: "《铝合金材料及其热处理技术》", 30 April 2012, 冶金工业出版社 * |
| 陆艳红: "均匀化制度对7055铝合金组织与力学性能的影响", 《中南大学硕士学位论文》 * |
Cited By (19)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107267898A (en) * | 2017-07-07 | 2017-10-20 | 哈尔滨中飞新技术股份有限公司 | A kind of 7075 aluminium alloy homogenising treatment methods |
| CN107723634A (en) * | 2017-10-24 | 2018-02-23 | 山东南山铝业股份有限公司 | Realize the heat treatment method and aviation alloyed aluminium sheet material of T77 three-step agings |
| CN107740013A (en) * | 2017-10-24 | 2018-02-27 | 山东南山铝业股份有限公司 | The three-step aging heat treatment method of aviation alloyed aluminium, the production method and aluminum alloy plate materials of aviation alloyed aluminium sheet material |
| CN107740013B (en) * | 2017-10-24 | 2019-10-18 | 山东南山铝业股份有限公司 | Heat treatment method, aluminum alloy plate materials and its production method of aviation alloyed aluminium |
| CN109055875A (en) * | 2018-10-27 | 2018-12-21 | 安徽创弘精密机械有限公司 | A kind of heat treatment process improving aluminium alloy extrusions intensity |
| CN110172653A (en) * | 2019-01-31 | 2019-08-27 | 苏州铭恒金属科技有限公司 | It is a kind of improve aluminium alloy cast ingot conductivity homogenizing method and the aluminium alloy cast ingot as made from the homogenizing method |
| CN111424197B (en) * | 2020-04-14 | 2021-12-21 | 广西南南铝加工有限公司 | Corrosion-resistant aluminum alloy for aviation and preparation method thereof |
| CN111424197A (en) * | 2020-04-14 | 2020-07-17 | 广西南南铝加工有限公司 | Corrosion-resistant aluminum alloy for aviation and preparation method thereof |
| CN111455239A (en) * | 2020-04-14 | 2020-07-28 | 广西南南铝加工有限公司 | Ultrahigh-strength aviation aluminum alloy and preparation method thereof |
| CN111455239B (en) * | 2020-04-14 | 2022-04-08 | 广西南南铝加工有限公司 | Ultrahigh-strength aviation aluminum alloy and preparation method thereof |
| CN111702009A (en) * | 2020-06-28 | 2020-09-25 | 山东南山铝业股份有限公司 | Preparation method of T4 or T42-state 2024 aluminum alloy coated aluminum sheet |
| CN111702009B (en) * | 2020-06-28 | 2022-05-06 | 山东南山铝业股份有限公司 | Preparation method of T4 or T42-state 2024 aluminum alloy coated aluminum sheet |
| CN111876702A (en) * | 2020-08-06 | 2020-11-03 | 西南铝业（集团）有限责任公司 | Solution quenching heat treatment process for industrially producing 7150 alloy thick plate |
| CN111926226B (en) * | 2020-08-12 | 2021-12-14 | 烟台南山学院 | High-strength plastic aluminum alloy and preparation method thereof |
| CN111926226A (en) * | 2020-08-12 | 2020-11-13 | 烟台南山学院 | High-strength plastic aluminum alloy and preparation method thereof |
| CN112553550A (en) * | 2020-11-23 | 2021-03-26 | 天津忠旺铝业有限公司 | Production process of 7-series aluminum alloy thick plate with high damage tolerance and low quenching sensitivity |
| CN112553550B (en) * | 2020-11-23 | 2021-12-28 | 天津忠旺铝业有限公司 | Production process of 7-series aluminum alloy thick plate with high damage tolerance and low quenching sensitivity |
| CN115491618A (en) * | 2022-09-23 | 2022-12-20 | 湖南中创空天新材料股份有限公司 | Aging heat treatment system for reducing anisotropy of aluminum alloy ring piece and improving comprehensive performance |
| CN115491618B (en) * | 2022-09-23 | 2023-12-15 | 湖南中创空天新材料股份有限公司 | Aging heat treatment system for reducing anisotropy of aluminum alloy ring piece and improving comprehensive performance |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106756675B (en) | 2019-01-18 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN106756675B (en) | Aviation alloyed aluminium plate and its production method | |
| CN108425050B (en) | High-strength high-toughness aluminum lithium alloy and preparation method thereof | |
| US11326241B2 (en) | Plastic wrought magnesium alloy and preparation method thereof | |
| CN101624671B (en) | Large-diameter 7005 aluminum alloy round ingot and preparation method thereof | |
| CN108823440B (en) | Preparation method and application of hypoeutectic aluminum-silicon alloy plate blank | |
| CN107723634A (en) | Realize the heat treatment method and aviation alloyed aluminium sheet material of T77 three-step agings | |
| CN109504884A (en) | Polynary a small amount of high-strength plasticity magnesium alloy and its heavy reduction short flow process | |
| CN106906390B (en) | Aluminium alloy anode oxide plate and its production method | |
| CN108220637A (en) | 5A03 aluminium alloy cast ingots production method and 5A03 aluminium alloy cast ingots and application | |
| CN105274399A (en) | Aluminum alloy material for cable conductor and application of material | |
| CN108531782A (en) | One kind Casting Al-Li Alloy containing magnesium and preparation method thereof | |
| CN106893909A (en) | A kind of aluminum alloy plate materials and preparation method thereof | |
| CN104404415A (en) | Preparation process of aviation aluminum alloy ingot and aluminum alloy ingot | |
| CN112210703B (en) | High-recrystallization-resistance and high-toughness aluminum lithium alloy and preparation method thereof | |
| CN106917017A (en) | Aluminum alloy plate materials and its production method | |
| CN115627396B (en) | Ultra-long aluminum alloy plate with ultrahigh strength, toughness and corrosion resistance and preparation method thereof | |
| CN113897567B (en) | Homogenization thermomechanical treatment method for rapidly refining and homogenizing cast aluminum-lithium alloy | |
| CN115710662A (en) | High-strength high-toughness aluminum lithium alloy plate and production process thereof | |
| CN104060138A (en) | Low-cost high-performance non-rare-earth magnesium alloy panel and preparation method thereof | |
| CN107513645A (en) | A kind of 8006 container aluminium foils and its production method | |
| Cao et al. | Effect of Al addition on the rolled microstructure and mechanical properties of Mg-4Y-3Nd alloys | |
| CN109182810B (en) | Low-cost high-room-temperature plastic deformation magnesium alloy and preparation method thereof | |
| CN117884587B (en) | Continuous casting and rolling method for aluminum alloy plate strip blank | |
| CN115612952B (en) | Method for producing large-size aluminum alloy medium-thickness wide plate by using large-size aluminum alloy ingot | |
| CN115505807B (en) | High-specific-strength aluminum lithium alloy and preparation method and application thereof |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| TA01 | Transfer of patent application right | ||
| TA01 | Transfer of patent application right |
Effective date of registration: 20181219 Address after: 265700 Longkou City Nanshan Industrial Park, Yantai, Shandong Applicant after: Shandong Nanshan Aluminium Co.,Ltd. Applicant after: HANGXIN MATERIAL TECHNOLOGY CO.,LTD. Address before: 265700 Qian Song Village, Dongjiang Town, Longkou City, Yantai, Shandong Applicant before: Shandong Nanshan Aluminium Co.,Ltd. Applicant before: Yantai Nanshan University |
|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| PE01 | Entry into force of the registration of the contract for pledge of patent right | ||
| PE01 | Entry into force of the registration of the contract for pledge of patent right |
Denomination of invention: Aluminum alloy sheet for aviation and its production method Effective date of registration: 20211117 Granted publication date: 20190118 Pledgee: Yantai Donghai aluminum foil Co.,Ltd. Pledgor: Shandong Nanshan Aluminium Co.,Ltd. Registration number: Y2021980012518 |
|
| PC01 | Cancellation of the registration of the contract for pledge of patent right | ||
| PC01 | Cancellation of the registration of the contract for pledge of patent right |
Date of cancellation: 20221031 Granted publication date: 20190118 Pledgee: Yantai Donghai aluminum foil Co.,Ltd. Pledgor: Shandong Nanshan Aluminium Co.,Ltd. Registration number: Y2021980012518 |