CN107164646A - A kind of preparation method of aluminum alloy materials - Google Patents
A kind of preparation method of aluminum alloy materials Download PDFInfo
- Publication number
- CN107164646A CN107164646A CN201710339767.0A CN201710339767A CN107164646A CN 107164646 A CN107164646 A CN 107164646A CN 201710339767 A CN201710339767 A CN 201710339767A CN 107164646 A CN107164646 A CN 107164646A
- Authority
- CN
- China
- Prior art keywords
- temperature
- aluminum alloy
- preparation
- alloy materials
- time
- 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.)
- Pending
Links
Classifications
-
- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21C—MANUFACTURE OF METAL SHEETS, WIRE, RODS, TUBES OR PROFILES, OTHERWISE THAN BY ROLLING; AUXILIARY OPERATIONS USED IN CONNECTION WITH METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL
- B21C37/00—Manufacture of metal sheets, bars, wire, tubes or like semi-manufactured products, not otherwise provided for; Manufacture of tubes of special shape
- B21C37/02—Manufacture of metal sheets, bars, wire, tubes or like semi-manufactured products, not otherwise provided for; Manufacture of tubes of special shape of sheets
-
- 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
-
- 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
Abstract
The present invention discloses a kind of preparation method of aluminum alloy materials, comprises the following steps：（1）Composition design；（2）Melting；（3）Casting；（4）Soaking；（5）Crop end, milling face；（6）Preheating；（7）Hot rolling；（8）Solution hardening；（9）Pre-stretching；（10）Timeliness；（11）Examine；（12）Finished product sawing.Wherein, the basic ingredient of the aluminum alloy materials includes the raw material of following weight percentage：Zn 8 ~ 12wt%, Mg 1.0 ~ 2.4wt%, Cu 0.05 ~ 0.25wt% of 0.4 ~ 2.2wt%, Zr, surplus is Al, also, 4.5≤Zn/Mg≤6,0.65≤Cu/Mg≤0.95.Performance of the new alloy of the present invention in terms of intensity, fracture toughness, electrical conductivity increases significantly.
Description
Technical field
The invention belongs to field of alloy material, it is related to a kind of preparation method of aluminum alloy materials, it is more particularly to a kind of high
The preparation method of the aluminum alloy materials of the high through hardening of strong high-ductility.
Background technology
The aluminum alloy plate materials of high-strength and high ductility, high through hardening and improved corrosion performance, are widely used in aerospace industry.Closely
With the requirement of aircraft loss of weight and security over year, aviation field begins to use large-scale integral aluminum alloy structural member, obtains
Good weight loss effect, security is also greatly improved.At the same time, it is necessary to the aluminium alloy plate of big size high-performance
Material, the thickness of required sheet material is more and more thicker.And sheet material is thicker, the performance difference of through-thickness is bigger, often slab central layer
Performance do not reach use requirement.Meanwhile, aluminium alloy thick plate, which is used for aircraft industry, also has " bucket effect ", due to slab central layer
Performance is not up to standard and limits the use to it.Therefore, 7000 line aluminium alloys of the high through hardening of high-strength and high ductility are aircrafts with large-scale whole
The critical material of body formula structural member manufacture.The aircraft structure of maximization and integration is to high-performance aluminium alloy Heavy plate production process
In thermal deformation and heat treatment link propose unprecedented challenge, wherein aluminium alloy thick plate quenching degree is exactly most fatal ask
One of topic.
And existing technical scheme, it is that by optimized alloy composition, Mg the and Cu elements that sensitivity is quenched in reduction alloy contain
Zn contents in amount, raising alloy, raising Zn/Mg ratios, strict control trace element Cr, Mn and Ti and Impurity Fe,
Si content, develops the aviation alloy of new generation by representative of 7085,7081 alloys, meets below thickness 300mm thick
Plate and the demand of forging manufacture.
Therefore, the shortcoming of prior art is mainly reflected in：
（1）Top layer mechanical property is slightly inadequate compared with the ripe trade mark such as 7050,7055 etc.；
（2）The demand of the following slabs of thickness 300mm and forging manufacture can only be met；
（3）Sheet metal thickness require below 100mm in the case of do not have clear superiority, be also not enough to completely substitution 7050,
7055 grade alloys in common use.
The content of the invention
To overcome the shortcoming that the mechanical property of aeronautical plate present in prior art is low, plank thickness is limited, the present invention
Purpose be to provide a kind of production method of innovation to prepare the high through hardening aluminum alloy materials of high-strength and high ductility, so as to improve its mechanical property
Can, and the aviation alloyed aluminium of slab and forging thickness more than 300mm can be manufactured.
To achieve the above object, the technical scheme that uses of the present invention is：
A kind of preparation method of aluminum alloy materials, comprises the following steps：
S1：Each metal material is taken by weight, and the composition composition and percentage by weight of each metal material are：Zn 8 ~ 12wt%, Mg
1.0 ~ 2.4wt%, Cu 0.05 ~ 0.25wt% of 0.4 ~ 2.2wt%, Zr, surplus is Al and inevitable impurity, also, 4.5≤
Zn/Mg≤6,0.65≤Cu/Mg≤0.95；
S2：Above-mentioned each metal material is all thrown melting is carried out to high temperature melting furnace, each gold is constantly adjusted in fusion process
Belong to the ratio of material, until meeting predetermined requirement；
S3：Molten metal obtained by step S2 is cast, ingot blank is obtained；
S4：Ingot blank obtained by step S3 is subjected to all heat-treated；
S5：By the excision end to end of the ingot blank obtained by step S4 and milling face is carried out, it is thick to be sawed into 400~600mm, 1500 ~ 2000mm
Wide blank；
S6：Blank obtained by step S5 is preheated 4 ~ 20 hours at 350~450 DEG C, ingot casting is obtained；
S7：By the ingot rolling obtained by step S6 into thickness be 50 ~ 400mm slab；
S8：Slab obtained by step S7 is sent to progress solution hardening processing in the stove of roller bottom；
S9：Sheet material obtained by step S8 is subjected to stretch processing, amount of tension is 1%~3%；
S10：Sheet material obtained by step S9 is subjected to Ageing Treatment；
S11：Sheet material obtained by step S10 is tested, qualified finished product sheet material is obtained；
S12：The specification of qualified finished product sheet material obtained by step S11 on demand is subjected to sawing.
It is preferred that, the composition composition and percentage by weight of each metal material are in the step S1：Zn 9 ~ 11wt%, Mg
1.2 ~ 2.2wt%, Cu 0.10 ~ 0.20wt% of 0.6 ~ 2.0wt%, Zr, surplus is Al and inevitable impurity, also, 4.5≤
Zn/Mg≤6,0.65≤Cu/Mg≤0.95.
It is preferred that, the fusion process in the step S2 includes degasification slagging-off process and filter progress.
It is preferred that, the casting in the step S3 uses the foundry engieering of Quench, wherein, casting temperature is 670 ~ 725 DEG C,
Casting speed is 30 ~ 50mm/min, and casting water-carrying capacity is 10 ~ 35m3/ h, casting water temperature is 15 ~ 35 DEG C.
It is preferred that, all heat-treated in the step S4 is using the multistage homogenization technology progressively heated up.
It is preferred that, the homogenization technology that the multistage progressively heats up is：The first order, 300~420 DEG C of temperature, time 12
~48h；The second level, 425~450 DEG C of temperature, 12~36h of time；The third level, 455~475 DEG C of temperature, the time 12~
24h；The fourth stage, 476~495 DEG C of temperature, 10~20h of time.
It is preferred that, all heat-treated in the step S4 using the high temperature again of low temperature after first high temperature homogenization technology.
It is preferred that, the homogenization technology of low temperature high temperature again is after the first high temperature：The first order, 400~470 DEG C of temperature, when
Between 16~48h；The second level, 250~400 DEG C of temperature, 24~72h of time；The third level, 450~485 DEG C of temperature, time 12
~36h.
It is preferred that, the holding temperature of solution hardening in step S8 processing is 450 ~ 490 DEG C, soaking time is 500 ~
1500min, during quenching, quenching room temperature is no more than 20 DEG C.
It is preferred that, the Ageing Treatment in the step S10 is specially：The first order, 40~120 DEG C of temperature, 2~36h of time；
The second level, 130~180 DEG C of temperature, 4~96h of time.
Compared with prior art, the beneficial effects of the invention are as follows：
（1）Alloy property such as intensity, fracture toughness, electrical conductivity etc. of this technology design are significantly improved, than existing 7085,
The performance of the alloys such as 7A85,7081 improves more than 5%；
（2）Slab or forging that the alloy designed using this technology is prepared into, its thickness can reach more than 300mm, and heart table
Performance difference is no more than 8%.
Brief description of the drawings
Fig. 1 is process chart of the invention；
New alloy and the depth-hardness curve comparison diagram of 7085,7050 alloys that Fig. 2 is prepared for the present invention；
New alloy and the hardness retention curve comparison figure of 7085,7050 alloys that Fig. 3 is prepared for the present invention.
Embodiment
A kind of preparation method of aluminum alloy materials, its processing step are as shown in figure 1, be specially：
S1：Each metal material is taken by weight, in order to ensure the high through hardening of the high-strength and high ductility of aluminum alloy materials, the composition of each metal material
Composition and percentage by weight are：Zn 8 ~ 12wt%, Mg 1.0 ~ 2.4wt%, Cu 0.4 ~ 2.2wt%, Zr 0.05 ~
0.25wt%, surplus is Al and inevitable impurity, while also needing to meet：4.5≤Zn/Mg≤6,0.65≤Cu/Mg≤
0.95；
S2：Above-mentioned each metal material is all thrown melting is carried out to high temperature melting furnace, each gold is constantly adjusted in fusion process
Belong to the ratio of material, until meeting predetermined requirement.Meanwhile, reduced in fusion process by multi-stage combination degasification slagging-off process
Hydrogen slag concentration in aluminum melt, to reduce the stomata or pin hole in ingot casting；By filter progress remove aluminum melt in oxide,
Non-metallic inclusion and other harmful metal impurities, to reduce the defects such as the loose, stomata in ingot casting, slag inclusion.In this manner it is possible to
Improve the quality of big size ingot-casting.
S3：Molten metal obtained by step S2 is cast, casting temperature, casting speed, casting are passed through in fusion-casting process
The collaboration optimization of water-carrying capacity, high-quality ingot blank is obtained using the foundry engieering of Quench.Wherein casting temperature is 670 ~ 725 DEG C,
Casting speed is 30 ~ 50mm/min, and casting water-carrying capacity is 10 ~ 35m3/ h, casting water temperature is 15 ~ 35 DEG C.
S4：Ingot blank obtained by step S3 is subjected to all heat-treated.After all heat-treated is using multistage progressively heating or first high temperature
The homogenization technology of low temperature high temperature again.Wherein, the multistage homogenization technology that progressively heats up is：The first order, temperature 300~420
DEG C, 12~48h of time；The second level, 425~450 DEG C of temperature, 12~36h of time；The third level, 455~475 DEG C of temperature, when
Between 12~24h；The fourth stage, 476~495 DEG C of temperature, 10~20h of time.And after first high temperature low temperature high temperature again homogenization skill
Art is：The first order, 400~470 DEG C of temperature, 16~48h of time；The second level, 250~400 DEG C of temperature, 24~72h of time；
The third level, 450~485 DEG C of temperature, 12~36h of time.Pass through all heat-treated, it is possible to eliminate remaining crystalline phase, obtain thin
The Al of small even dispersion3Zr particles.
S5：By the excision end to end of the ingot blank obtained by step S4 and milling face is carried out, it is thick to be sawed into 400~600mm, 1500 ~
Blank wide 2000mm；
S6：Blank obtained by step S5 is preheated 4 ~ 20 hours at 350~450 DEG C, ingot casting is obtained；
S7：Severe deformation technology is used to be rolled into slab of the thickness for 50 ~ 400mm on the ingot casting obtained by step S6；
S8：Slab obtained by step S7 is sent to progress solution hardening processing in the stove of roller bottom.Wherein, the holding temperature of solid solution is
450 ~ 490 DEG C, soaking time is 500 ~ 1500min, during quenching, and quenching room temperature is no more than 20 DEG C.
S9：Sheet material obtained by step S8 is subjected to stretch processing using stretching-machine, amount of tension is 1%~3%；
S10：Sheet material obtained by step S9 is subjected to Ageing Treatment.Ageing Treatment is divided into two-stage, wherein, the temperature of the first order is 40
~120 DEG C, the time is 2~36h；130~180 DEG C of the temperature of the second level, the time is 4~96h.By such Ageing Treatment
Afterwards, it is possible to improve the combination property of sheet material.
S11：Sheet material obtained by step S10 is tested, qualified finished product sheet material is obtained；
S12：The specification of qualified finished product sheet material obtained by step S11 on demand is subjected to sawing.
Embodiment one
It is 60mm to produce finished product gauge thickness, and width is 1800mm, and length is 6000mm slab, and process is as follows：
（1）Following metal material is weighed by weight percentage and is put into smelting furnace：Zn 8 ~ 12wt%, Mg 1.0 ~
2.4wt%, Cu 0.05 ~ 0.25wt% of 0.4 ~ 2.2wt%, Zr, surplus are Al and inevitable impurity, also, 4.5≤Zn/Mg
≤ 6,0.65≤Cu/Mg≤0.95.
（2）Smelting aluminium alloy, after deaerated, filtering, carries out semi-continuous casting, and it is 520mm slab ingot and equal to cast out thickness
Heat.
（3）By slab cut end tail and milling face, by preheating and rolling, the slab that thickness is 60mm is prepared.
（4）30mm × 30mm × 140mm end quenching samples are cut on the top layer of slab.
（5）By end quenching sample after 475 DEG C of solid solution 180min, quenched in end quenching equipment, after pass through
After 110 DEG C/6h+150 DEG C/12h timeliness, depth-hardness curve is measured, and is contrasted with the depth-hardness curve of 7085 and 7050 alloys,
As a result as shown in Figures 2 and 3, it can be seen that new alloy, 7085 alloys and 7050 alloy two ends prepared by the present invention
Hardness difference be respectively 5.8%, 8.8% and 12%.
Embodiment two
It is 60mm to produce finished product gauge thickness, and width is 1800mm, and length is 6000mm slab, and process is as follows：
（1）Following metal material is weighed by weight percentage and is put into smelting furnace：Zn 9 ~ 11wt%, Mg 1.2 ~
2.2wt%, Cu 0.10 ~ 0.20wt% of 0.6 ~ 2.0wt%, Zr, surplus are Al and inevitable impurity, also, 4.5≤Zn/Mg
≤ 6,0.65≤Cu/Mg≤0.95.
（2）Smelting aluminium alloy, after deaerated, filtering, carries out semi-continuous casting, and it is 520mm slab ingot and equal to cast out thickness
Heat.
（3）By slab cut end tail and milling face, by preheating and rolling, the slab that thickness is 60mm is prepared.
（4）Sheet material is quenched after 470 DEG C of solid solution 180min, the aligning that deflection is 2.5% is carried out afterwards, through 110
DEG C/6h+160 DEG C/12h timeliness after, detect performance, and with 7085 and 7050 alloy plate performance comparisons, as a result as shown in table 1.
1 three kinds of alloy plate (60mm) T7451 of table performance comparison
| Alloy | Tensile strength/MPa | Yield strength/MPa | Elongation percentage/% | Fracture toughness/MPam1/2 | Electrical conductivity/%IACS | Heart difference is different/% |
| New alloy | 545 | 521 | 9.5 | 38 | 42.5 | 4 |
| 7085 | 512 | 490 | 11 | 34.5 | 41 | 5.5 |
| 7050 | 532 | 505 | 9 | 32 | 40.5 | 8 |
Embodiment three
It is 200mm to produce finished product gauge thickness, and width is 1800mm, and length is 6000mm ultra-thick plate, and process is as follows：
（1）Following metal material is weighed by weight percentage and is put into smelting furnace：Zn 8 ~ 12wt%, Mg 1.0 ~
2.4wt%, Cu 0.05 ~ 0.25wt% of 0.4 ~ 2.2wt%, Zr, surplus are Al and inevitable impurity, also, 4.5≤Zn/Mg
≤ 6,0.65≤Cu/Mg≤0.95.
（2）Smelting aluminium alloy, after deaerated, filtering, carries out semi-continuous casting, and it is 520mm slab ingot and equal to cast out thickness
Heat.
（3）By slab cut end tail and milling face, by preheating and rolling, the ultra-thick plate that thickness is 200mm is prepared.
（4）Sheet material is quenched after 470 DEG C of solid solution 600min, the aligning that deflection is 2.5% is carried out afterwards, through 110
DEG C/6h+160 DEG C/12h timeliness after, detect performance, and with 7085 and 7050 alloy plate performance comparisons, as shown in table 2.
2 three kinds of alloy ultra-thick plate (200mm) T7451 of table central layer performance comparison
| Alloy | Tensile strength/MPa | Yield strength/MPa | Elongation percentage/% | Fracture toughness/MPam1/2 | Electrical conductivity/%IACS | Heart difference is different/% |
| New alloy | 535 | 516 | 9 | 36 | 43.2 | 5 |
| 7085 | 500 | 480 | 10 | 31.5 | 42.5 | 8 |
| 7050 | 465 | 419 | 7.5 | 27 | 41.5 | 15 |
Example IV
It is 350mm to produce finished product gauge thickness, and width is 1800mm, and length is 6000mm pole slab, and process is as follows：
（1）Following metal material is weighed by weight percentage and is put into smelting furnace：Zn 9 ~ 11wt%, Mg 1.2 ~
2.2wt%, Cu 0.10 ~ 0.20wt% of 0.6 ~ 2.0wt%, Zr, surplus are Al and inevitable impurity, also, 4.5≤Zn/Mg
≤ 6,0.65≤Cu/Mg≤0.95.
（2）Smelting aluminium alloy, after deaerated, filtering, carries out semi-continuous casting, and it is 520mm slab ingot and equal to cast out thickness
Heat.
（3）By slab cut end tail and milling face, by preheating and rolling, the pole slab that thickness is 350mm is prepared.
（4）Sheet material is quenched after 470 DEG C of solid solution 1200min, the aligning that deflection is 2.5%, warp are carried out afterwards
After 110 DEG C/6h+160 DEG C/12h timeliness, performance is detected, as shown in table 3.
Table 3 new alloy pole slab (350mm) T7451 central layer performance
| Alloy | Tensile strength/MPa | Yield strength/MPa | Elongation percentage/% | Fracture toughness/MPam1/2 | Electrical conductivity/%IACS | Heart difference is different/% |
| New alloy | 524 | 504 | 8.5 | 34.5 | 44.5 | 6 |
The new alloy of the present invention increases significantly in the performances such as intensity, fracture toughness, electrical conductivity, than existing 7085,
The performance of the alloys such as 7A85,7081 improves more than 5%；And the slab or forging that it is prepared, thickness can reach more than 300mm,
And heart table performance difference is no more than 8%.
Claims (10)
1. a kind of preparation method of aluminum alloy materials, it is characterised in that comprise the following steps：
S1：Each metal material is taken by weight, and the composition composition and percentage by weight of each metal material are：Zn 8 ~ 12wt%, Mg
1.0 ~ 2.4wt%, Cu 0.05 ~ 0.25wt% of 0.4 ~ 2.2wt%, Zr, surplus is Al and inevitable impurity, also, 4.5≤
Zn/Mg≤6,0.65≤Cu/Mg≤0.95；
S2：Above-mentioned each metal material is all thrown melting is carried out to high temperature melting furnace, each gold is constantly adjusted in fusion process
Belong to the ratio of material, until meeting predetermined requirement；
S3：Molten metal obtained by step S2 is cast, ingot blank is obtained；
S4：Ingot blank obtained by step S3 is subjected to all heat-treated；
S5：By the excision end to end of the ingot blank obtained by step S4 and milling face is carried out, it is thick to be sawed into 400~600mm, 1500 ~ 2000mm
Wide blank；
S6：Blank obtained by step S5 is preheated 4 ~ 20 hours at 350~450 DEG C, ingot casting is obtained；
S7：By the ingot rolling obtained by step S6 into thickness be 50 ~ 400mm slab；
S8：Slab obtained by step S7 is sent to progress solution hardening processing in the stove of roller bottom；
S9：Sheet material obtained by step S8 is subjected to stretch processing, amount of tension is 1%~3%；
S10：Sheet material obtained by step S9 is subjected to Ageing Treatment；
S11：Sheet material obtained by step S10 is tested, qualified finished product sheet material is obtained；
S12：The specification of qualified finished product sheet material obtained by step S11 on demand is subjected to sawing.
2. the preparation method of a kind of aluminum alloy materials according to claim 1, it is characterised in that each in the step S1
The composition of metal material is constituted and percentage by weight is：Zn 9 ~ 11wt%, Mg 1.2 ~ 2.2wt%, Cu 0.6 ~ 2.0wt%, Zr
0.10 ~ 0.20wt%, surplus is Al and inevitable impurity, also, 4.5≤Zn/Mg≤6,0.65≤Cu/Mg≤0.95.
3. the preparation method of a kind of aluminum alloy materials according to claim 1, it is characterised in that molten in the step S2
Refining process includes degasification slagging-off process and filter progress.
4. a kind of preparation method of aluminum alloy materials according to claim 1, it is characterised in that the casting in the step S3
The foundry engieering using Quench is made, wherein, casting temperature is 670 ~ 725 DEG C, and casting speed is 30 ~ 50mm/min, casts current
Measure as 10 ~ 35m3/ h, casting water temperature is 15 ~ 35 DEG C.
5. the preparation method of a kind of aluminum alloy materials according to claim 1, it is characterised in that equal in the step S4
Heat treatment is using the multistage homogenization technology progressively heated up.
6. the preparation method of a kind of aluminum alloy materials according to claim 5, it is characterised in that the multistage progressively heats up
Homogenization technology be：The first order, 300~420 DEG C of temperature, 12~48h of time；The second level, 425~450 DEG C of temperature, when
Between 12~36h；The third level, 455~475 DEG C of temperature, 12~24h of time；The fourth stage, 476~495 DEG C of temperature, time 10
~20h.
7. the preparation method of a kind of aluminum alloy materials according to claim 1, it is characterised in that equal in the step S4
Heat treatment using the high temperature again of low temperature after first high temperature homogenization technology.
8. a kind of preparation method of aluminum alloy materials according to claim 7, it is characterised in that low temperature after the first high temperature
The homogenization technology of high temperature is again：The first order, 400~470 DEG C of temperature, 16~48h of time；The second level, temperature 250~400
DEG C, 24~72h of time；The third level, 450~485 DEG C of temperature, 12~36h of time.
9. a kind of preparation method of aluminum alloy materials according to claim 1, it is characterised in that consolidating in the step S8
The holding temperature of molten Quenching Treatment is 450 ~ 490 DEG C, and soaking time is 500 ~ 1500min, during quenching, and quenching room temperature is no more than 20
℃。
10. the preparation method of a kind of aluminum alloy materials according to claim 1, it is characterised in that in the step S10
Ageing Treatment is specially：The first order, 40~120 DEG C of temperature, 2~36h of time；The second level, 130~180 DEG C of temperature, the time 4~
96h。
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710339767.0A CN107164646A (en) | 2017-05-15 | 2017-05-15 | A kind of preparation method of aluminum alloy materials |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710339767.0A CN107164646A (en) | 2017-05-15 | 2017-05-15 | A kind of preparation method of aluminum alloy materials |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107164646A true CN107164646A (en) | 2017-09-15 |
Family
ID=59816761
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710339767.0A Pending CN107164646A (en) | 2017-05-15 | 2017-05-15 | A kind of preparation method of aluminum alloy materials |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107164646A (en) |
Cited By (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107937847A (en) * | 2017-12-29 | 2018-04-20 | 西南铝业（集团）有限责任公司 | A kind of homogenizing heat treatment of the strong 7 line aluminium alloy material of superelevation for heavy haul train draw bar |
| CN107964615A (en) * | 2017-11-22 | 2018-04-27 | 华南理工大学 | A kind of extrudate high-strength 7xxx line aluminium alloys and preparation method thereof |
| CN108149095A (en) * | 2017-12-29 | 2018-06-12 | 西南铝业（集团）有限责任公司 | A kind of production method of the strong 7 line aluminium alloy material of inexpensive superelevation for heavy haul train draw bar |
| CN108179332A (en) * | 2017-12-29 | 2018-06-19 | 西南铝业（集团）有限责任公司 | A kind of strong 7 line aluminium alloy material of inexpensive superelevation for heavy haul train draw bar and its production method |
| CN108220845A (en) * | 2017-12-29 | 2018-06-29 | 西南铝业（集团）有限责任公司 | A kind of solid solution aging technique of the strong 7 line aluminium alloy material of superelevation for heavy haul train draw bar |
| CN108300915A (en) * | 2018-01-24 | 2018-07-20 | 中南大学 | A kind of Al-Zn-Mg-Cu systems aerolite and preparation method thereof |
| CN108385003A (en) * | 2018-05-23 | 2018-08-10 | 东北轻合金有限责任公司 | A kind of aerospace high-ductility corrosion aluminium alloy extrusions and preparation method thereof |
| CN108381117A (en) * | 2018-01-24 | 2018-08-10 | 广西南南铝加工有限公司 | A kind of heat-treatable strengthened aluminum alloy soldering technique |
| CN108611583A (en) * | 2018-05-30 | 2018-10-02 | 上海交通大学 | The heat treatment method of titanium boride particle enhanced aluminum-based composite material Strengthening and Toughening in situ |
| CN109266879A (en) * | 2018-11-20 | 2019-01-25 | 天津百恩威新材料科技有限公司 | A kind of Bradley bistrique and high-strength aluminum alloy are preparing the application in Bradley bistrique |
| CN110423906A (en) * | 2019-08-17 | 2019-11-08 | 桂林理工大学 | A kind of preparation method of 120 mm thickness aluminium alloy thick plate |
| CN110699576A (en) * | 2019-10-24 | 2020-01-17 | 广西南南铝加工有限公司 | Preparation process of high-strength aluminum alloy precision casting plate |
| CN113182379A (en) * | 2021-07-01 | 2021-07-30 | 中国航发北京航空材料研究院 | Preparation method of aluminum alloy plate |
| CN113564434A (en) * | 2021-08-12 | 2021-10-29 | 四川福蓉科技股份公司 | 7-series aluminum alloy and preparation method thereof |
| CN113737068A (en) * | 2021-08-19 | 2021-12-03 | 中铝材料应用研究院有限公司 | High-strength and high-toughness corrosion-resistant 7xxx series aluminum alloy and processing method thereof |
| CN115710662A (en) * | 2022-11-21 | 2023-02-24 | 郑州轻研合金科技有限公司 | High-strength high-toughness aluminum lithium alloy plate and production process thereof |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101698914A (en) * | 2009-11-13 | 2010-04-28 | 中国航空工业集团公司北京航空材料研究院 | Novel ultra-high-strength aluminum alloy and preparation method thereof |
| CN102108463A (en) * | 2010-01-29 | 2011-06-29 | 北京有色金属研究总院 | Aluminium alloy product suitable for manufacturing structures and preparation method |
| CN102732761A (en) * | 2012-06-18 | 2012-10-17 | 中国航空工业集团公司北京航空材料研究院 | 7000 series aluminum alloy material and preparation method thereof |
| CN104109784A (en) * | 2014-04-30 | 2014-10-22 | 广西南南铝加工有限公司 | Ultrahigh-strength Al-Zn-Mg-Cu system aluminum alloy large-size flat cast ingot and making method thereof |
| CN104711465A (en) * | 2015-04-09 | 2015-06-17 | 东南大学 | Al-Zn-Mg-Cu high-strength aluminum alloy material and preparation method thereof |
| CN105506421A (en) * | 2015-12-31 | 2016-04-20 | 广西南南铝加工有限公司 | Al-Zn-Mg aluminum alloy medium-thick plate and preparation method thereof |
-
2017
- 2017-05-15 CN CN201710339767.0A patent/CN107164646A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101698914A (en) * | 2009-11-13 | 2010-04-28 | 中国航空工业集团公司北京航空材料研究院 | Novel ultra-high-strength aluminum alloy and preparation method thereof |
| CN102108463A (en) * | 2010-01-29 | 2011-06-29 | 北京有色金属研究总院 | Aluminium alloy product suitable for manufacturing structures and preparation method |
| CN102732761A (en) * | 2012-06-18 | 2012-10-17 | 中国航空工业集团公司北京航空材料研究院 | 7000 series aluminum alloy material and preparation method thereof |
| CN104109784A (en) * | 2014-04-30 | 2014-10-22 | 广西南南铝加工有限公司 | Ultrahigh-strength Al-Zn-Mg-Cu system aluminum alloy large-size flat cast ingot and making method thereof |
| CN104711465A (en) * | 2015-04-09 | 2015-06-17 | 东南大学 | Al-Zn-Mg-Cu high-strength aluminum alloy material and preparation method thereof |
| CN105506421A (en) * | 2015-12-31 | 2016-04-20 | 广西南南铝加工有限公司 | Al-Zn-Mg aluminum alloy medium-thick plate and preparation method thereof |
Cited By (20)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107964615A (en) * | 2017-11-22 | 2018-04-27 | 华南理工大学 | A kind of extrudate high-strength 7xxx line aluminium alloys and preparation method thereof |
| CN107937847A (en) * | 2017-12-29 | 2018-04-20 | 西南铝业（集团）有限责任公司 | A kind of homogenizing heat treatment of the strong 7 line aluminium alloy material of superelevation for heavy haul train draw bar |
| CN108149095A (en) * | 2017-12-29 | 2018-06-12 | 西南铝业（集团）有限责任公司 | A kind of production method of the strong 7 line aluminium alloy material of inexpensive superelevation for heavy haul train draw bar |
| CN108179332A (en) * | 2017-12-29 | 2018-06-19 | 西南铝业（集团）有限责任公司 | A kind of strong 7 line aluminium alloy material of inexpensive superelevation for heavy haul train draw bar and its production method |
| CN108220845A (en) * | 2017-12-29 | 2018-06-29 | 西南铝业（集团）有限责任公司 | A kind of solid solution aging technique of the strong 7 line aluminium alloy material of superelevation for heavy haul train draw bar |
| CN108300915A (en) * | 2018-01-24 | 2018-07-20 | 中南大学 | A kind of Al-Zn-Mg-Cu systems aerolite and preparation method thereof |
| CN108381117A (en) * | 2018-01-24 | 2018-08-10 | 广西南南铝加工有限公司 | A kind of heat-treatable strengthened aluminum alloy soldering technique |
| CN108385003A (en) * | 2018-05-23 | 2018-08-10 | 东北轻合金有限责任公司 | A kind of aerospace high-ductility corrosion aluminium alloy extrusions and preparation method thereof |
| CN108385003B (en) * | 2018-05-23 | 2019-01-18 | 东北轻合金有限责任公司 | A kind of aerospace high-ductility corrosion aluminium alloy extrusions and preparation method thereof |
| CN108611583A (en) * | 2018-05-30 | 2018-10-02 | 上海交通大学 | The heat treatment method of titanium boride particle enhanced aluminum-based composite material Strengthening and Toughening in situ |
| CN109266879A (en) * | 2018-11-20 | 2019-01-25 | 天津百恩威新材料科技有限公司 | A kind of Bradley bistrique and high-strength aluminum alloy are preparing the application in Bradley bistrique |
| CN110423906A (en) * | 2019-08-17 | 2019-11-08 | 桂林理工大学 | A kind of preparation method of 120 mm thickness aluminium alloy thick plate |
| CN110699576A (en) * | 2019-10-24 | 2020-01-17 | 广西南南铝加工有限公司 | Preparation process of high-strength aluminum alloy precision casting plate |
| CN110699576B (en) * | 2019-10-24 | 2021-04-13 | 广西南南铝加工有限公司 | Preparation process of high-strength aluminum alloy precision casting plate |
| CN113182379A (en) * | 2021-07-01 | 2021-07-30 | 中国航发北京航空材料研究院 | Preparation method of aluminum alloy plate |
| CN113564434A (en) * | 2021-08-12 | 2021-10-29 | 四川福蓉科技股份公司 | 7-series aluminum alloy and preparation method thereof |
| CN113564434B (en) * | 2021-08-12 | 2022-03-22 | 四川福蓉科技股份公司 | 7-series aluminum alloy and preparation method thereof |
| CN113737068A (en) * | 2021-08-19 | 2021-12-03 | 中铝材料应用研究院有限公司 | High-strength and high-toughness corrosion-resistant 7xxx series aluminum alloy and processing method thereof |
| CN115710662A (en) * | 2022-11-21 | 2023-02-24 | 郑州轻研合金科技有限公司 | High-strength high-toughness aluminum lithium alloy plate and production process thereof |
| CN115710662B (en) * | 2022-11-21 | 2024-02-06 | 郑州轻研合金科技有限公司 | High-strength high-toughness aluminum lithium alloy plate and production process thereof |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN107164646A (en) | A kind of preparation method of aluminum alloy materials | |
| CN108425050B (en) | High-strength high-toughness aluminum lithium alloy and preparation method thereof | |
| CA2700250C (en) | Al-cu-li alloy product suitable for aerospace application | |
| CN110449541A (en) | A kind of free forging rod billet of GH4169 high temperature alloy and preparation method thereof | |
| US8877123B2 (en) | Al—Cu alloy product suitable for aerospace application | |
| US20080173377A1 (en) | Aa7000-series aluminum alloy products and a method of manufacturing thereof | |
| CN104388777A (en) | High-strength aluminum alloy slab and manufacturing method thereof | |
| WO2013114928A1 (en) | Forged aluminum alloy material and method for producing same | |
| EP2274454B1 (en) | Alloy composition and preparation thereof | |
| CN110042333A (en) | A kind of manufacturing method of 625MPa grades of large-size aluminum alloy pre-stretching plates of aviation | |
| CN104959393A (en) | Production method of aluminium alloy hot extrusion bar used for high-quality aviation blade | |
| US20210404037A1 (en) | 7xxx-series aluminium alloy product | |
| CN105803280A (en) | Damage resisting tolerance high-strength aluminum alloy plate and preparation method thereof | |
| CN109487116B (en) | High-strength titanium-copper alloy strip suitable for conductive elastic component and preparation method thereof | |
| CN113667912B (en) | Large-size aluminum alloy plate and preparation method thereof | |
| CN114480922B (en) | Ultra-light aluminum-lithium alloy and preparation method and application thereof | |
| CN110629083A (en) | Marine 5083 aluminum alloy plate and processing technology thereof | |
| US20210207254A1 (en) | Al-Cu-Li-Mg-Mn-Zn ALLOY WROUGHT PRODUCT | |
| CN110714147B (en) | 6082 aluminum alloy plate for aviation and preparation process thereof | |
| KR20130097665A (en) | Copper alloy | |
| KR20150047246A (en) | Method for manufacturing of Al-Zn-Mg-Cu alloy sheet with refined crystal grains | |
| CN108977689B (en) | Metastable beta titanium alloy plate and processing method thereof | |
| CN111041311A (en) | Rare earth magnesium alloy with low cost and high performance and preparation technology thereof | |
| CN109022958A (en) | A kind of manufacturing method of 5083 aluminium alloy thick plate peculiar to vessel | |
| KR101757733B1 (en) | Method for manufacturing of Al-Zn-Mg-Cu alloy sheet with refined crystal grains |
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 | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20170915 |
|
| WD01 | Invention patent application deemed withdrawn after publication |