CN107740012A - A kind of aerolite forging part preparation method - Google Patents
A kind of aerolite forging part preparation method Download PDFInfo
- Publication number
- CN107740012A CN107740012A CN201710959337.9A CN201710959337A CN107740012A CN 107740012 A CN107740012 A CN 107740012A CN 201710959337 A CN201710959337 A CN 201710959337A CN 107740012 A CN107740012 A CN 107740012A
- Authority
- CN
- China
- Prior art keywords
- forging
- aerolite
- forging part
- part preparation
- rolling
- 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.)
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Classifications
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
- C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
- C22F1/04—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
-
- 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
- C22F1/002—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working by rapid cooling or quenching; cooling agents used therefor
Abstract
The invention discloses a kind of aerolite forging part preparation method, first, the ingot casting for the first pre-set dimension for meeting requirement is rolled, and the default passage of rolling, so that hot rolled plate of the ingot rolling into the second pre-set dimension, by large-scale forging part substep sectional forming, solve the problems, such as that equipment oversteps the extreme limit；Then, finish-forging is carried out to hot rolled plate so that the default angle of hot rolling plate benging, turn into forging, solve the problems, such as that flat-die forging cogging can not meet forging part uniformity as blank using hot rolled plate due to the present invention；Then, forging is subjected to Quenching Treatment；Then, the forging by quenching is subjected to stretch processing, turns into tensioning member, the present invention carries out cold stretch to forging part by hydraulic press and cuts down residual stress, solves forging part compression cold deformation residual stress and cuts down insufficient, uneven problem；Finally, tensioning member is subjected to Ageing Treatment, turns into aerolite forging part.
Description
Technical field
The present invention relates to forging part rolling technical field, more particularly, to a kind of aerolite forging part preparation method.
Background technology
Large aluminum alloy arc forging part is the crucial bearing member that aircraft wing is connected with fuselage, and its dimensions is big, long
Spend 5.6m, projected area 4.1m2, forging part piece weight is more than 1 ton；Complex-shaped, machinability requires high, machining
It is irregular curved surface or herring-bone form afterwards, thickness is 5mm~8mm, it is desirable to which maximum patch die clearance is no more than 6mm, in 200mm length
Gap difference is no more than 0.2mm, and lateral bending deflection degree is no more than 1mm, be current largest domestic, the requirement of most complicated, combination property most
High aluminum alloy die forgings.
At present, traditional forging part is typically 1 shaping, and aerolite forging part exceeds the equipment limit, tradition side
Method can not produce；By the way of base is forged, charge length needed for such large-scale arc forging part reaches traditional forging part
To 6 meters, base low production efficiency is forged, and uniformity is poor can not meet forging part technical requirements；Traditional forging cold pressing
The method abatement quenched residual stress of compression deformation, the especially big arc forging of such aluminium alloy are remaining using cold compression and deformation abatement quenching
Stress can not ensure forging part size, and the later stage, orthopedic meeting additional stress caused machining deformation, can not use.
Therefore, how to produce and meet that the aerolite forging part of requirement is that those skilled in the art are urgently to be resolved hurrily
Technical problem.
The content of the invention
In view of this, it is an object of the invention to provide a kind of aerolite forging part preparation method, can produce full
The aerolite forging part of sufficient requirement.
To achieve these goals, the invention provides following scheme：
A kind of aerolite forging part preparation method, comprises the following steps：
Step A：The ingot casting of first pre-set dimension is rolled, and rolls default passage so that the ingot rolling
Into the hot rolled plate of the second pre-set dimension；
Step B：Finish-forging is carried out to the hot rolled plate so that the default angle of hot rolling plate benging, turn into forging；
Step C：The forging is subjected to Quenching Treatment；
Step D：Forging by quenching is carried out by cold stretch processing by hydraulic press, turns into tensioning member；
Step E：The tensioning member is subjected to Ageing Treatment, turns into aerolite forging part.
Preferably, in above-mentioned aerolite forging part preparation method, also include before the step A：
Step F：The ingot casting is indulged in Hot Line and pushes away 400 DEG C -420 DEG C of stove heat, and is incubated 4 hours.
Preferably, in above-mentioned aerolite forging part preparation method, the default passage of rolling in the step A is
First passage and second time sum；
Wherein, first passage is the passage of the transverse rolling first rolled；
The passage for the axial rolling that second passage rolls afterwards for it.
Preferably, in above-mentioned aerolite forging part preparation method, start rolling temperature in the step A for 390 DEG C-
410 DEG C, finishing temperature is more than or equal to 350 DEG C.
Preferably, in above-mentioned aerolite forging part preparation method, also wrapped between the step A and the step B
Include：
Step G：Cut the net hot rolled plate end to end with broadside on fish tail and layering.
Preferably, in above-mentioned aerolite forging part preparation method, also wrapped between the step G and the step B
Include：
Step H：The finish-forging die that finish-forging is carried out to the hot rolled plate is heated, 250 DEG C -450 DEG C of heating-up temperature, is at least heated
14 hours；
The hot rolled plate is heated, heating-up temperature is 350 DEG C -400 DEG C, is incubated -510 minutes 85 minutes.
Preferably, in above-mentioned aerolite forging part preparation method, during the finish-forging in the step B, forging is opened
Temperature is 330 DEG C -400 DEG C, and final forging temperature is more than or equal to 300 DEG C.
Preferably, in above-mentioned aerolite forging part preparation method, hardening heat in the step C for 472 DEG C-
482 DEG C, air thermal preservation 360 minutes quenches 60 DEG C -70 DEG C of water temperature, and quenching shift time is less than or equal to 25 seconds.
Preferably, in above-mentioned aerolite forging part preparation method, the stretching in the step D is small in quenching 12
When interior completion.
Preferably, in above-mentioned aerolite forging part preparation method, Ageing Treatment is protected for first air in the step E
116 DEG C -126 DEG C of temperature, it is incubated 6 hours；Then 172 DEG C -182 DEG C of air thermal preservation, 6 hours are incubated.
It can be seen from the above technical scheme that aerolite forging part preparation method disclosed by the invention, first, will
Meet that the ingot casting of the first pre-set dimension of requirement is rolled, and roll default passage so that ingot rolling is into second
The hot rolled plate of pre-set dimension, because a point multiple passages roll to ingot casting, large-scale forging part substep sectional forming solves
The problem of equipment oversteps the extreme limit；Then, finish-forging is carried out to hot rolled plate so that the default angle of hot rolling plate benging, turn into forging, by
Solve the problems, such as that flat-die forging cogging can not meet forging part uniformity as blank using hot rolled plate in the present invention；Then, will
Forging carries out Quenching Treatment；Then, the forging by quenching is subjected to stretch processing, turns into tensioning member, the present invention passes through hydraulic pressure
Machine carries out cold stretch abatement residual stress to forging part, and it is insufficient, uneven to solve forging part compression cold deformation residual stress abatement
Even problem；Finally, tensioning member is subjected to Ageing Treatment, turns into aerolite forging part.In summary, method of the invention
It can realize and produce the aerolite forging part for meeting requirement.
Brief description of the drawings
In order to illustrate more clearly about the embodiment of the present invention or technical scheme of the prior art, below will be to embodiment or existing
There is the required accompanying drawing used in technology description to be briefly described, it should be apparent that, drawings in the following description are only this
Some embodiments of invention, for those of ordinary skill in the art, on the premise of not paying creative work, can be with
Other accompanying drawings are obtained according to these accompanying drawings.
Fig. 1 is the aerolite forging part preparation method flow chart that the embodiment of the present invention one provides；
Fig. 2 is the aerolite forging part preparation method flow chart that the embodiment of the present invention two provides.
Embodiment
In order that those skilled in the art is better understood from technical scheme, it is below in conjunction with the accompanying drawings and specific real
Applying mode, the present invention is described in further detail.
Embodiment one
As shown in figure 1, the invention discloses a kind of aerolite forging part preparation method, comprise the following steps：
Step S1：By the default passage of the ingot rolling of selection, turn into hot rolled plate.
The ingot casting of first pre-set dimension is rolled, and rolls default passage so that ingot rolling is default into second
The hot rolled plate of size.
Specifically include：Stock, the cast ingot dimension of selection is the first default size, and here, the first default size can
To be set as needed, in the present embodiment, the first default size of ingot casting is：350mm*1300mm*3450mm, and ingot casting
Material be 7050, chemical composition meets the requirement of Q/SWAJ5022-2009 (the ingot casting quality certification fills in YMS1121).
First transverse rolling broadening is to 1750+20Mm, then axial rolling is to 85±1Mm is thick.Roll final size：10000+500×1750+20×
85±1。
Rolling pass state modulator is as follows：
Transverse rolling reduction distribution 340 → 330 → 320 → 310 → 300 → 290 → 280 → 270 → 264；
Axial rolling reduction distribution 250 → 235 → 220 → 190 → 155 → 120 → 85.5.
Step S2：Finish-forging is carried out to hot rolled plate so that the default angle of hot rolling plate benging, turn into forging.
The equipment that finish-forging uses for：30000 tons of hydraulic presses match somebody with somebody bearing plate, F327 finish-forging dies.
Finish-forging scheme：Hot rolled plate is produced flexural deformation, do not produce metal flow；The center of hot rolled plate is first pressed, so
Afterwards again respectively to two ends pressing mold, it is not necessary to which upper pressure only (can ensure web thickness by hydraulic press deadweight pressing mold
More than 83mm).Side stand rearways are forged, forbidding to keep flat prevents from deforming.
Here, the angle of setting is actually needed according to the default angle of hot rolling plate benging.
Step S3：Forging is subjected to Quenching Treatment.
The stirring of ON cycle water terminates until quenching before quenching, should lift the material for holding forging after forging quenching water-inlet immediately
Frame is not less than 10 minutes, and forging can not expose the surface and (cancel the operation of lifting material frame after quenching tank transformation) in whole process, water
Middle immersion more than 16 minutes.
Step S4：Forging by quenching is carried out by cold stretch processing by hydraulic press, turns into tensioning member.
Stretch the equipment that uses for：3# machines, F327 drawing dies.Stretching, extensibility are completed after quenching in 12 hours
1.5%-3%.The record stretching data on card.The extensibility in addition to chuck is detected, after being stretched with F904 models inspection record
Radian situation of change.
Step S5：Tensioning member is subjected to Ageing Treatment, turns into aerolite forging part.
Furnace charge by downwind it is edge-on it is equidirectional put, be spaced more than 500mm.First stage：121 ± 5 DEG C, air thermal preservation
6 hours；Second stage：177 ± 5 DEG C, air thermal preservation 6 hours.
Aerolite forging part preparation method disclosed by the invention, first, the first default chi of requirement will be met
Very little ingot casting is rolled, and rolls default passage so that ingot rolling into the second pre-set dimension hot rolled plate, due to point more
Individual passage rolls to ingot casting, by large-scale forging part substep sectional forming, solves the problems, such as that equipment oversteps the extreme limit；Then,
Finish-forging is carried out to hot rolled plate so that the default angle of hot rolling plate benging, turn into forging, due to the present invention using hot rolled plate as base
Material, solves the problems, such as that flat-die forging cogging can not meet forging part uniformity；Then, forging is subjected to Quenching Treatment；Then, will
Forging by quenching carries out stretch processing, turns into tensioning member, and the present invention carries out cold stretch abatement by hydraulic press to forging part
Residual stress, solve forging part compression cold deformation residual stress and cut down insufficient, uneven problem；Finally, tensioning member is entered
Row Ageing Treatment, turn into aerolite forging part.To sum up, method of the invention, which can be realized to produce, meets requirement
Aerolite forging part.
Embodiment two
Referring to Fig. 2, in second embodiment provided by the invention, aerolite forging part preparation method and embodiment one
In aerolite forging part preparation method it is similar, something in common is just repeated no more, only introduces difference.
In the present embodiment, also include before disclosing step S1：
Step S6：Ingot casting is indulged in Hot Line and pushes away 400 DEG C -420 DEG C of stove heat, and is incubated 4 hours.
Further, disclose also includes between step S1 and step S2：
Step S7：Cut net hot rolled plate end to end with broadside on fish tail and layering.
Hot rolled plate plate is cut into the net fish tail with broadside and layering end to end, 1 cuts 2 slabs to size 7200+100×726+15×
85±1mm。
Further, the invention discloses also include between step S7 and step S2：
Step S8：The finish-forging die and hot rolled plate that finish-forging is carried out to hot rolled plate are heated respectively.
Mould heats：F327 finish-forging dies, 250~450 DEG C, at least heat 14 hours.
Blank heating：350~400 DEG C (380 DEG C of constant temperatures), it is incubated 85~510 minutes.
Specifically, it is the first passage and second time sum the invention discloses the default passage of the rolling in step S1,
Wherein, the first passage is the passage of the transverse rolling first rolled；The passage for the axial rolling that second passage rolls afterwards for it.
It it is 390 DEG C -410 DEG C the invention also discloses the start rolling temperature in step S1, finishing temperature is more than or equal to 350
℃。
During the finish-forging in step S2, starting forging temperature is 330 DEG C -400 DEG C, and final forging temperature is more than
Or equal to 300 DEG C.
Hardening heat in step S3 is 472 DEG C -482 DEG C, air thermal preservation 360 minutes, quenches 60 DEG C -70 DEG C of water temperature, quenches
Fiery transfer time is less than or equal to 25 seconds.
Stretching in step S4 is completed in 12 hours in quenching.
Ageing Treatment is first 116 DEG C -126 DEG C of air thermal preservation in step S5, is incubated 6 hours；Then 172 DEG C of air thermal preservation-
182 DEG C, it is incubated 6 hours.
" first " in the present invention, " second " etc. are to be distinguished in description, without other particular meanings.
The foregoing description of the disclosed embodiments, professional and technical personnel in the field are enable to realize or using the present invention.
A variety of modifications to these embodiments will be apparent for those skilled in the art, as defined herein
General Principle can be realized in other embodiments without departing from the spirit or scope of the present invention.Therefore, it is of the invention
The embodiments shown herein is not intended to be limited to, and is to fit to and principles disclosed herein and inventive features phase
Consistent most wide scope.
Claims (10)
1. a kind of aerolite forging part preparation method, it is characterised in that comprise the following steps：
Step A：The ingot casting of first pre-set dimension is rolled, and rolls default passage so that the ingot rolling is into the
The hot rolled plate of two pre-set dimensions；
Step B：Finish-forging is carried out to the hot rolled plate so that the default angle of hot rolling plate benging, turn into forging；
Step C：The forging is subjected to Quenching Treatment；
Step D：Forging by quenching is carried out by cold stretch processing by hydraulic press, turns into tensioning member；
Step E：The tensioning member is subjected to Ageing Treatment, turns into aerolite forging part.
2. aerolite forging part preparation method according to claim 1, it is characterised in that before the step A also
Including：
Step F：The ingot casting is indulged in Hot Line and pushes away 400 DEG C -420 DEG C of stove heat, and is incubated 4 hours.
3. aerolite forging part preparation method according to claim 1, it is characterised in that rolling in the step A
Default passage is made as the first passage and second time sum；
Wherein, first passage is the passage of the transverse rolling first rolled；
The passage for the axial rolling that second passage rolls afterwards for it.
4. aerolite forging part preparation method according to claim 1, it is characterised in that opening in the step A
Temperature is rolled for 390 DEG C -410 DEG C, and finishing temperature is more than or equal to 350 DEG C.
5. aerolite forging part preparation method according to claim 1, it is characterised in that the step A and described
Also include between step B：
Step G：Cut the net hot rolled plate end to end with broadside on fish tail and layering.
6. aerolite forging part preparation method according to claim 5, it is characterised in that the step G and described
Also include between step B：
Step H：The finish-forging die that finish-forging is carried out to the hot rolled plate is heated, 250 DEG C -450 DEG C of heating-up temperature, at least heats 14
Hour；
The hot rolled plate is heated, heating-up temperature is 350 DEG C -400 DEG C, is incubated -510 minutes 85 minutes.
7. aerolite forging part preparation method according to claim 1, it is characterised in that the end in the step B
In forging process, starting forging temperature is 330 DEG C -400 DEG C, and final forging temperature is more than or equal to 300 DEG C.
8. aerolite forging part preparation method according to claim 1, it is characterised in that quenching in the step C
Fiery temperature is 472 DEG C -482 DEG C, air thermal preservation 360 minutes, quenches 60 DEG C -70 DEG C of water temperature, quenching shift time is less than or waited
In 25 seconds.
9. aerolite forging part preparation method according to claim 1, it is characterised in that the drawing in the step D
Stretch quenching 12 hours in complete.
10. the aerolite forging part preparation method according to any one in claim 1-9, it is characterised in that institute
It is first 116 DEG C -126 DEG C of air thermal preservation to state Ageing Treatment in step E, is incubated 6 hours；Then 172 DEG C -182 DEG C of air thermal preservation, protect
Warm 6 hours.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710959337.9A CN107740012B (en) | 2017-10-16 | 2017-10-16 | A kind of aerolite forging part preparation method |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710959337.9A CN107740012B (en) | 2017-10-16 | 2017-10-16 | A kind of aerolite forging part preparation method |
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| Publication Number | Publication Date |
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| CN107740012A true CN107740012A (en) | 2018-02-27 |
| CN107740012B CN107740012B (en) | 2019-08-06 |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109108196A (en) * | 2018-07-25 | 2019-01-01 | 东北轻合金有限责任公司 | A kind of preparation method of aircraft wing high-strength/tenacity aluminum alloy forging part |
| CN109234653A (en) * | 2018-10-23 | 2019-01-18 | 湖南大学 | A method of cutting down large complicated aluminum alloy die forgings residual stress |
| CN110453163A (en) * | 2019-08-16 | 2019-11-15 | 中国航发北京航空材料研究院 | A method of 7000 line aluminium alloy super large-scale forging part height are improved to performance |
| CN112872256A (en) * | 2020-12-28 | 2021-06-01 | 西南铝业（集团）有限责任公司 | Production process of 7039 alloy super-wide plate forging |
| CN112893724A (en) * | 2020-12-28 | 2021-06-04 | 西南铝业（集团）有限责任公司 | Isothermal die forging forming process for precision die forging of passenger observation window frame |
Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1780926A (en) * | 2003-04-10 | 2006-05-31 | 克里斯铝轧制品有限公司 | Al-zn-mg-cu alloy |
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2017
- 2017-10-16 CN CN201710959337.9A patent/CN107740012B/en active Active
Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1780926A (en) * | 2003-04-10 | 2006-05-31 | 克里斯铝轧制品有限公司 | Al-zn-mg-cu alloy |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109108196A (en) * | 2018-07-25 | 2019-01-01 | 东北轻合金有限责任公司 | A kind of preparation method of aircraft wing high-strength/tenacity aluminum alloy forging part |
| CN109234653A (en) * | 2018-10-23 | 2019-01-18 | 湖南大学 | A method of cutting down large complicated aluminum alloy die forgings residual stress |
| CN109234653B (en) * | 2018-10-23 | 2020-07-07 | 湖南大学 | Method for reducing residual stress of large complex aluminum alloy die forging |
| CN110453163A (en) * | 2019-08-16 | 2019-11-15 | 中国航发北京航空材料研究院 | A method of 7000 line aluminium alloy super large-scale forging part height are improved to performance |
| CN112872256A (en) * | 2020-12-28 | 2021-06-01 | 西南铝业（集团）有限责任公司 | Production process of 7039 alloy super-wide plate forging |
| CN112893724A (en) * | 2020-12-28 | 2021-06-04 | 西南铝业（集团）有限责任公司 | Isothermal die forging forming process for precision die forging of passenger observation window frame |
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|---|---|
| CN107740012B (en) | 2019-08-06 |
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