CN103589924A - Production process for aluminum alloy bar used for aviation structural component - Google Patents
Production process for aluminum alloy bar used for aviation structural component Download PDFInfo
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- CN103589924A CN103589924A CN201310627688.1A CN201310627688A CN103589924A CN 103589924 A CN103589924 A CN 103589924A CN 201310627688 A CN201310627688 A CN 201310627688A CN 103589924 A CN103589924 A CN 103589924A
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Abstract
The invention discloses a production process for an aluminum alloy bar used for an aviation structural component. The process comprises the following steps: component optimization; casting for blank making; extrusion molding; quenching and stretching; and aging treatment. After optimization, an aluminum alloy comprises (by mass), 0.22 to 0.28% of Si, 0.38 to 0.42% of Fe, 1.50 to 1.70% of Cu, 0.22 to 0.28% of Mn, 2.50 to 2.70% of Mg, 0.18 to 0.26% of Cr, 5.55 to 5.75% of Zn, 0.10 to 0.20% of Ti and 0.01 to 0.06% of Zr, with the balance being Al. During extrusion molding, an extrusion speed is 0.6 to 1.0 m/min, cast bar temperature is 420 +/- 10 DEG C, die temperature is 450 +/- 10 DEG C, and the temperature of an extrusion container is 400 +/- 10 DEG C. The aluminum alloy bar produced by using the method has excellent comprehensive mechanical properties and high conductivity.
Description
Technical field
The invention belongs to aluminium alloy and manufacture field, relate to a kind of technique of producing rods and bars of aluminium alloy, particularly a kind of technique of producing aerospace component use rods and bars of aluminium alloy.
Background technology
It is light that aluminium alloy has quality, and intensity is high, and wear resistance is good, and the advantage such as not yielding after processing is very extensive in field application such as automobile, aerospace, shippings.Aluminium alloy is commonly used to produce aerospace component, and still, conventional production technique cannot meet the requirement of aerospace component to indexs such as rods and bars of aluminium alloy metallographic structure, mechanical properties, particularly cannot well regulate and control rods and bars of aluminium alloy specific conductivity and mechanical property.
Therefore, be necessary to develop the technique of rods and bars of aluminium alloy for a kind of new production aerospace component.
Summary of the invention
In view of this, the object of the present invention is to provide a kind of technique of rods and bars of aluminium alloy for aerospace component of producing, the rods and bars of aluminium alloy mechanical property of this explained hereafter is excellent, and specific conductivity is high.
For achieving the above object, the invention provides following technical scheme:
A kind of technique of producing aerospace component use rods and bars of aluminium alloy, comprise optimizing components, cast base, extrusion molding, quenching stretching and ageing treatment step, after optimizing components, al alloy component is as follows: Si:0.22-0.28wt%, Fe:0.38-0.42wt%, Cu:1.50%～1.70wt%, Mn:0.22-0.28wt%, Mg:2.50%～2.70wt%, Cr:0.18%～0.26wt%, Zn:5.55%～5.75wt%, Ti:0.10-0.20wt%, Zr:0.01-0.06wt%, Al: surplus, wherein Ti+Zr:<0.23wt%; In described extrusion molding step, extrusion speed is 0.6-1.0m/min, and during extrusion molding, casting rod temperature is 420 ℃ ± 10 ℃, and die temperature is 450 ℃ ± 10 ℃, and container temperature is 400 ℃ ± 10 ℃.
Further, quenching stretching concrete steps are as follows:
1) by extruding after section bar be heated to 455-465 ℃ after cold quenching;
2) stretching step 1) section bar after quenching, this step extensibility is 1.5%～2%;
3) by step 2) section bar after stretching be heated to 460-465 ℃ after cold quenching;
4) stretching step 3) section bar after quenching, this step extensibility is 1.8-2.2%.
Further, step 1) quenching preincubation 95-105min, step 3) quenching preincubation 145-155min.
Further, ageing treatment time-divisions two step is carried out, and the first step aging temp is 95-105 ℃, and aging time is 7.7-8.5h; The first step completes carries out second step, and second step aging temp is 165-175 ℃, and aging time is 13.5-14.5h.
Further, after optimizing components, al alloy component is as follows: Si:0.25wt%, Fe:0.4wt%, Cu:1.55%～1.65wt%, Mn:0.25wt%, Mg:2.55%～2.65wt%, Cr:0.19%～0.25wt%, Zn:5.6%～5.7wt%, Ti:0.15wt%, Zr:0.03wt%, Al: surplus.
Beneficial effect of the present invention is: adopt method of the present invention to produce the comprehensive mechanical property excellence of rods and bars of aluminium alloy, its tensile strength can reach 531MPa, and yield strength can reach 467MPa, and unit elongation can reach 13%; The conductivity of the rods and bars of aluminium alloy that the present invention produces is excellent, and specific conductivity can reach 22.58MS/m, meets the application demand of aeronautical product completely.
Embodiment
Below the preferred embodiments of the present invention are described in detail.
Embodiment 1:
The present embodiment is produced the technique of rods and bars of aluminium alloy for aerospace component, comprise optimizing components, cast base, extrusion molding, quenching stretching and ageing treatment step, after optimizing components, al alloy component is as follows: Si:0.22wt%, Fe:0.42wt%, Cu:1.50wt%, Mn:0.28wt%, Mg:2.50wt%, Cr:0.26wt%, Zn:5.55wt%, Ti:0.20wt%, Zr:0.01wt%, Al: surplus; In described extrusion molding step, extrusion speed is 0.6m/min, and during extrusion molding, casting rod temperature is 430 ℃, and die temperature is 440 ℃, and container temperature is 390 ℃.
As the improvement of the present embodiment, quenching stretching concrete steps are as follows:
1) section bar after extruding is heated to 455 rear cold quenchings;
2) stretching step 1) section bar after quenching, this step extensibility is 1.5%;
3) by step 2) section bar after stretching be heated to 465 ℃ after cold quenching;
4) stretching step 3) section bar after quenching, this step extensibility is 2.2%.
As the improvement of the present embodiment, step 1) quenching preincubation 105min, step 3) quenching preincubation 145min.
As the improvement of the present embodiment, ageing treatment time-divisions two step is carried out, and the first step aging temp is 95 ℃, and aging time is 8.5h; The first step completes carries out second step, and second step aging temp is 165 ℃, and aging time is 14.5h.
Embodiment 2:
The present embodiment is produced the technique of rods and bars of aluminium alloy for aerospace component, comprise optimizing components, cast base, extrusion molding, quenching stretching and ageing treatment step, after optimizing components, al alloy component is as follows: Si:0.28wt%, Fe:0.38wt%, Cu:1.70wt%, Mn:0.22wt%, Mg:2.70wt%, Cr:0.18%, Zn:5.75wt%, Ti:0.10wt%, Zr:0.06wt%, Al: surplus; In described extrusion molding step, extrusion speed is 1.0m/min, and during extrusion molding, casting rod temperature is 430 ℃, and die temperature is 460 ℃, and container temperature is 410 ℃.
As the improvement of the present embodiment, quenching stretching concrete steps are as follows:
1) by extruding after section bar be heated to 465 ℃ after cold quenching;
2) stretching step 1) section bar after quenching, this step extensibility is 2%;
3) by step 2) section bar after stretching is heated to 460 rear cold quenchings;
4) stretching step 3) section bar after quenching, this step extensibility is 1.8%.
As the improvement of the present embodiment, step 1) quenching preincubation 95min, step 3) quenching preincubation 155min.
As the improvement of the present embodiment, ageing treatment time-divisions two step is carried out, and the first step aging temp is 105 ℃, and aging time is 7.5h; The first step completes carries out second step, and second step aging temp is 175 ℃, and aging time is 13.5h.
Embodiment 3:
The present embodiment is produced the technique of rods and bars of aluminium alloy for aerospace component, comprise optimizing components, cast base, extrusion molding, quenching stretching and ageing treatment step, after optimizing components, al alloy component is as follows: Si:0.25wt%, Fe:0.4wt%, Cu:1.55wt%, Mn:0.25wt%, Mg:2.65wt%, Cr:0.19wt%, Zn:5.7wt%, Ti:0.15wt%, Zr:0.03wt%, Al: surplus; In described extrusion molding step, extrusion speed is 0.7m/min, and during extrusion molding, casting rod temperature is 415 ℃, and die temperature is 455 ℃, and container temperature is 395 ℃.
As the improvement of the present embodiment, quenching stretching concrete steps are as follows:
1) by extruding after section bar be heated to 460 ℃ after cold quenching;
2) stretching step 1) section bar after quenching, this step extensibility is 1.7%;
3) by step 2) section bar after stretching be heated to 463 ℃ after cold quenching;
4) stretching step 3) section bar after quenching, this step extensibility is 2.0%.
As the improvement of the present embodiment, step 1) quenching preincubation 103min, step 3) quenching preincubation 147min.
As the improvement of the present embodiment, ageing treatment time-divisions two step is carried out, and the first step aging temp is 98 ℃, and aging time is 8.2h; The first step completes carries out second step, and second step aging temp is 173 ℃, and aging time is 13.7h.
Embodiment 4:
The present embodiment is produced the technique of rods and bars of aluminium alloy for aerospace component, comprise optimizing components, cast base, extrusion molding, quenching stretching and ageing treatment step, after optimizing components, al alloy component is as follows: Si:0.25wt%, Fe:0.4wt%, Cu:1.65wt%, Mn:0.25wt%, Mg:2.55wt%, Cr:0.25wt%, Zn:5.6wt%, Ti:0.15wt%, Zr:0.03wt%, Al: surplus; In described extrusion molding step, extrusion speed is 0.6-1.0m/min, and during extrusion molding, casting rod temperature is 425 ℃, and die temperature is 445 ℃, and container temperature is 405 ℃.
As the improvement of the present embodiment, quenching stretching concrete steps are as follows:
1) by extruding after section bar be heated to 464 ℃ after cold quenching;
2) stretching step 1) section bar after quenching, this step extensibility is 1.9%;
3) by step 2) section bar after stretching be heated to 462 ℃ after cold quenching;
4) stretching step 3) section bar after quenching, this step extensibility is 1.9%.
As the improvement of the present embodiment, step 1) quenching preincubation 97min, step 3) quenching preincubation 153min.
As the improvement of the present embodiment, ageing treatment time-divisions two step is carried out, and the first step aging temp is 103 ℃, and aging time is 7.7h; The first step completes carries out second step, and second step aging temp is 167 ℃, and aging time is 14.3h.
Embodiment 5:
The present embodiment is produced the technique of rods and bars of aluminium alloy for aerospace component, comprise optimizing components, cast base, extrusion molding, quenching stretching and ageing treatment step, after optimizing components, al alloy component is as follows: Si:0.25wt%, Fe:0.4wt%, Cu:1.60wt%, Mn:0.25wt%, Mg:2.60wt%, Cr:0.23wt%, Zn:5.65wt%, Ti:0.15wt%, Zr:0.03wt%, Al: surplus; In described extrusion molding step, extrusion speed is 0.8m/min, and during extrusion molding, casting rod temperature is 420 ℃, and die temperature is 450 ℃, and container temperature is 400 ℃.
As the improvement of the present embodiment, quenching stretching concrete steps are as follows:
1) by extruding after section bar be heated to 462 ℃ after cold quenching;
2) stretching step 1) section bar after quenching, this step extensibility is 1.8%;
3) by step 2) section bar after stretching be heated to 462 ℃ after cold quenching;
4) stretching step 3) section bar after quenching, this step extensibility is 1.8-2.2%.
As the improvement of the present embodiment, step 1) quenching preincubation 100min, step 3) quenching preincubation 150min.
As the improvement of the present embodiment, ageing treatment time-divisions two step is carried out, and the first step aging temp is 100 ℃, and aging time is 8h; The first step completes carries out second step, and second step aging temp is 170 ℃, and aging time is 14h.
Empirical tests, the beneficial effect of the present invention that above-described embodiment is produced is: above-described embodiment adopts method of the present invention to produce the comprehensive mechanical property excellence of rods and bars of aluminium alloy, and tensile strength can reach 531MPa, and yield strength can reach 467MPa, and unit elongation can reach 13%; The conductivity of the rods and bars of aluminium alloy that the present invention produces is excellent, and specific conductivity can reach 22.58MS/m, meets the application demand of aeronautical product completely.
Finally explanation is, above preferred embodiment is only unrestricted in order to technical scheme of the present invention to be described, although the present invention is described in detail by above preferred embodiment, but those skilled in the art are to be understood that, can to it, make various changes in the form and details, and not depart from the claims in the present invention book limited range.
Claims (5)
1. produce the technique of rods and bars of aluminium alloy for aerospace component for one kind, comprise optimizing components, cast base, extrusion molding, quench and stretch and ageing treatment step, it is characterized in that: after optimizing components, al alloy component is as follows: Si:0.22-0.28wt%, Fe:0.38-0.42wt%, Cu:1.50%～1.70wt%, Mn:0.22-0.28wt%, Mg:2.50%～2.70wt%, Cr:0.18%～0.26wt%, Zn:5.55%～5.75wt%, Ti:0.10-0.20wt%, Zr:0.01-0.06wt%, Al: surplus, Ti+Zr:<0.23wt% wherein, in described extrusion molding step, extrusion speed is 0.6-1.0m/min, and during extrusion molding, casting rod temperature is 420 ℃ ± 10 ℃, and die temperature is 450 ℃ ± 10 ℃, and container temperature is 400 ℃ ± 10 ℃.
2. produce according to claim 1 the technique of rods and bars of aluminium alloy for aerospace component, it is characterized in that, quenching stretching concrete steps are as follows:
1) by extruding after section bar be heated to 455-465 ℃ after cold quenching;
2) stretching step 1) section bar after quenching, this step extensibility is 1.5%～2%;
3) by step 2) section bar after stretching be heated to 460-465 ℃ after cold quenching;
4) stretching step 3) section bar after quenching, this step extensibility is 1.8-2.2%.
3. produce according to claim 2 the technique of rods and bars of aluminium alloy for aerospace component, it is characterized in that: step 1) quenching preincubation 95-105min, step 3) quenching preincubation 145-155min.
4. produce according to claim 1 the technique of rods and bars of aluminium alloy for aerospace component, it is characterized in that: ageing treatment time-divisions two step is carried out, the first step aging temp is 95-105 ℃, and aging time is 7.7-8.5h; The first step completes carries out second step, and second step aging temp is 165-175 ℃, and aging time is 13.5-14.5h.
5. according to producing the technique of aerospace component with rods and bars of aluminium alloy described in claim 1-4 any one, it is characterized in that: after optimizing components, al alloy component is as follows: Si:0.25wt%, Fe:0.4wt%, Cu:1.55%～1.65wt%, Mn:0.25wt%, Mg:2.55%～2.65wt%, Cr:0.19%～0.25wt%, Zn:5.6%～5.7wt%, Ti:0.15wt%, Zr:0.03wt%, Al: surplus.
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| CN104438420A (en) * | 2014-12-12 | 2015-03-25 | 西南铝业（集团）有限责任公司 | Preparation method of I beam profile |
| CN106239038A (en) * | 2016-07-29 | 2016-12-21 | 余姚市婉珍五金厂 | A kind of Tapered Cup liquid extrusion molding technique |
| CN106334787A (en) * | 2016-10-24 | 2017-01-18 | 三峡大学 | Gradient graphite/aluminum base surface layer self-lubrication composite and preparing method |
| CN106513456A (en) * | 2016-11-16 | 2017-03-22 | 辽宁忠旺集团有限公司 | High-strength 2024 aluminum alloy thin-wall angle profile production process |
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| CN107159729A (en) * | 2017-05-12 | 2017-09-15 | 辽宁忠旺集团有限公司 | The automobile-used 7A52 aluminium alloy pipes extrusion process of military armor |
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| CN102268621B (en) * | 2011-09-09 | 2013-03-20 | 西南铝业（集团）有限责任公司 | Production method of aluminium alloy bar |
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| CN104438420A (en) * | 2014-12-12 | 2015-03-25 | 西南铝业（集团）有限责任公司 | Preparation method of I beam profile |
| CN106239038A (en) * | 2016-07-29 | 2016-12-21 | 余姚市婉珍五金厂 | A kind of Tapered Cup liquid extrusion molding technique |
| CN106334787A (en) * | 2016-10-24 | 2017-01-18 | 三峡大学 | Gradient graphite/aluminum base surface layer self-lubrication composite and preparing method |
| CN106334787B (en) * | 2016-10-24 | 2018-06-29 | 三峡大学 | A kind of gradient graphite/aluminium base surface layer self-lubricating composite and preparation method |
| CN106513456A (en) * | 2016-11-16 | 2017-03-22 | 辽宁忠旺集团有限公司 | High-strength 2024 aluminum alloy thin-wall angle profile production process |
| CN106702233A (en) * | 2016-12-20 | 2017-05-24 | 辽宁忠旺集团有限公司 | Production process for manufacturing high-surface demand aircraft component by 7003-T6 aluminum alloy |
| CN107159729A (en) * | 2017-05-12 | 2017-09-15 | 辽宁忠旺集团有限公司 | The automobile-used 7A52 aluminium alloy pipes extrusion process of military armor |
| CN107282667A (en) * | 2017-07-07 | 2017-10-24 | 哈尔滨中飞新技术股份有限公司 | A kind of aluminium alloy extruded techniques of high-elongation 2A12 |
| CN107282667B (en) * | 2017-07-07 | 2019-02-19 | 哈尔滨中飞新技术股份有限公司 | A kind of aluminium alloy extruded technique of high-elongation 2A12 |
| CN109097647A (en) * | 2018-09-07 | 2018-12-28 | 山东兖矿轻合金有限公司 | A kind of variable diameter drill pipe body anticorodal and its manufacturing method |
| CN109097647B (en) * | 2018-09-07 | 2020-07-07 | 山东兖矿轻合金有限公司 | High-strength corrosion-resistant aluminum alloy for reducing drill pipe body and manufacturing method thereof |
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