CN105385972A - Aging process for 7075 aluminum alloy forge pieces - Google Patents
Aging process for 7075 aluminum alloy forge pieces Download PDFInfo
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- CN105385972A CN105385972A CN201510954534.2A CN201510954534A CN105385972A CN 105385972 A CN105385972 A CN 105385972A CN 201510954534 A CN201510954534 A CN 201510954534A CN 105385972 A CN105385972 A CN 105385972A
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- aluminum alloy
- alloy forge
- forge pieces
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
- C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
- C22F1/04—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon
- C22F1/053—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon of alloys with zinc as the next major constituent
Abstract
The invention relates to the technical field of 7075 aluminum alloy forge pieces and provides an aging process for the 7075 aluminum alloy forge pieces. The aging process is characterized by comprising a first stage, wherein the7075 aluminum alloy forge pieces are heated to 110 DEG C and the temperature is maintained for 4 hours; a second stage, wherein the 7075 aluminum alloy forge pieces subjected to the first stage are heated to 135 DEG C and the temperature is maintained for 3 hours; a third stage, wherein the 7075 aluminum alloy forge pieces subjected to the second stage are heated to 175 DEG C and the temperature is maintained for 3 hours. According to the aging process, the aging treatment time can be effectively shortened, the product production efficiency can be improved, and the cost can be reduced.
Description
Technical field
The present invention relates to manufacture 7075 aluminum alloy forge piece technical field, particularly relate to a kind of aging technique for 7075 aluminum alloy forge pieces.
Background technology
7075 belong to current domestic and international widely used high strength ultralumin, it is the main raw of aircraft structure, be applicable to manufacture aircraft skin, spar, bulkhead, landing gear components, and hydraulic system components etc., the heavily stressed structure unit of high strength and good corrosion resistance is also required for other.
At present, existing 7075 aluminum alloy forge piece institutions of prescription are generally single-stage aging (120 DEG C/24 hours) or the two-stage time effect (first step: 115 DEG C/12 hours; The second stage: 160 DEG C/6 hours), no matter be single-stage aging, or two-stage time effect, all there is the long problem that expends time in, and the length that expends time in has a strong impact on products production efficiency, and cause ageing treatment cost higher.Therefore, how to improve the aging technique of 7075 aluminum alloy forge pieces, aging time is shortened becomes those skilled in the art's technical problem urgently to be resolved hurrily.
Summary of the invention
In view of this, the invention provides a kind of aging technique for 7075 aluminum alloy forge pieces, this aging technique can shorten aging time, cost-saving.
In order to achieve the above object, the invention provides following technical scheme:
For an aging technique for 7075 aluminum alloy forge pieces, comprising:
Described 7075 aluminum alloy forge pieces are heated to 110 DEG C by the first step, keep 4 hours;
7075 aluminum alloy forge pieces after the described first step are heated to 135 DEG C by the second stage, keep 3 hours;
7075 aluminum alloy forge pieces behind the described second stage are heated to 175 DEG C by the third stage, keep 3 hours.
According to technique scheme, aging technique provided by the invention adopts three-step aging process to 7075 aluminum alloy forge pieces, aging time at different levels is respectively 4 hours, 3 hours, 3 hours, compared with prior art, aging technique provided by the invention effectively can shorten aging time, is conducive to improving products production efficiency and cost-saving.
Accompanying drawing explanation
In order to be illustrated more clearly in the embodiment of the present invention or technical scheme of the prior art, be briefly described to the accompanying drawing used required in embodiment or description of the prior art below, apparently, accompanying drawing in the following describes is only embodiments of the invention, for those of ordinary skill in the art, under the prerequisite not paying creative work, other accompanying drawing can also be obtained according to the accompanying drawing provided.
Fig. 1 is the schema of a kind of aging technique for 7075 aluminum alloy forge pieces that the embodiment of the present invention one provides;
Fig. 2 is the schema of the 7075 aluminum alloy forge piece ageing treatment that comparative example one of the present invention uses;
Fig. 3 is the schema of the 7075 aluminum alloy forge piece ageing treatment that comparative example two of the present invention uses.
Embodiment
For the ease of understanding, below in conjunction with accompanying drawing, the invention will be further described.
See Fig. 1, be the schema of a kind of aging technique for 7075 aluminum alloy forge pieces that the embodiment of the present invention one provides, specifically comprise:
7075 aluminum alloy forge pieces are heated to 110 DEG C by step S11, keep 4 hours;
7075 aluminum alloy forge pieces are heated to 135 DEG C by step S12, keep 3 hours;
7075 aluminum alloy forge pieces are heated to 175 DEG C by step S13, keep 3 hours.
After the three-step aging process of embodiment one, detect the mechanical property of 7075 aluminum alloy forge pieces, mechanical property is tested on CSS-44100 universal electrical tensile testing machine, and GB228-87 preparation pressed by sample, get long to being tension test direction, draw speed is 1mm/min.
Test result is: tensile strength 575MPa, yield strength 496MPa, unit elongation 10.8%.
See Fig. 2 and Fig. 3, in order to contrast, invention has been the ageing treatment of comparative example one and comparative example two, and test by the mechanical property of the detection method in the embodiment of the present invention one to 7075 aluminum alloy forge pieces after ageing treatment.
See Fig. 2, be the schema of the 7075 aluminum alloy forge piece ageing treatment that comparative example one uses, be specially: step S2,7075 aluminum alloy forge pieces are heated to 120 DEG C, keep 24 hours.
Comparative example one is single-stage aging, and the test result after ageing treatment is: tensile strength 563MPa, yield strength 489MPa, unit elongation 10.2%.
See Fig. 3, be the schema of the 7075 aluminum alloy forge piece ageing treatment that comparative example two uses, specifically comprise:
7075 aluminum alloy forge pieces are heated to 115 DEG C by step S31, keep 12 hours;
7075 aluminum alloy forge pieces are heated to 160 DEG C by step S32, keep 6 hours.
Comparative example two is two-stage time effect, and the test result after ageing treatment is: tensile strength 552MPa, yield strength 473MPa, unit elongation 11.6%.
As can be seen from the test result of embodiment one, comparative example one and comparative example two, aging technique of the present invention can obtain 7075 aluminum alloy forge pieces of the equal mechanical property level with prior art.Aging technique provided by the invention adopts three-step aging process to 7075 aluminum alloy forge pieces, aging time at different levels is respectively 4 hours, 3 hours, 3 hours, compared with prior art, aging technique provided by the invention effectively can shorten aging time, is conducive to improving products production efficiency and cost-saving.
It should be noted that, by standard GB/T/T3880.2-2006, product standard requires the maximum tensile strength 515MPa, yield strength 440MPa, unit elongation 8%.Visible aging technique provided by the invention can obtain the product meeting national standard.
To the above-mentioned explanation of the disclosed embodiments, professional and technical personnel in the field are realized or uses the present invention.To be apparent for those skilled in the art to the multiple amendment of embodiment, General Principle as defined herein can without departing from the spirit or scope of the present invention, realize in other embodiments.Therefore, the present invention can not be restricted to embodiment illustrated herein, but will meet the widest scope consistent with principle disclosed herein and features of novelty.
Claims (1)
1. for an aging technique for 7075 aluminum alloy forge pieces, it is characterized in that, comprising:
Described 7075 aluminum alloy forge pieces are heated to 110 DEG C by the first step, keep 4 hours;
7075 aluminum alloy forge pieces after the described first step are heated to 135 DEG C by the second stage, keep 3 hours;
7075 aluminum alloy forge pieces behind the described second stage are heated to 175 DEG C by the third stage, keep 3 hours.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510954534.2A CN105385972B (en) | 2015-12-17 | 2015-12-17 | It is a kind of to be used for the aging technique of 7075 aluminum alloy forge pieces |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510954534.2A CN105385972B (en) | 2015-12-17 | 2015-12-17 | It is a kind of to be used for the aging technique of 7075 aluminum alloy forge pieces |
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| CN105385972A true CN105385972A (en) | 2016-03-09 |
| CN105385972B CN105385972B (en) | 2017-09-26 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107937842A (en) * | 2017-12-01 | 2018-04-20 | 中南大学 | A kind of heat treatment method of Al Zn Mg Cu aluminium alloys |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4305763A (en) * | 1978-09-29 | 1981-12-15 | The Boeing Company | Method of producing an aluminum alloy product |
| JP2003277898A (en) * | 2002-03-27 | 2003-10-02 | Society Of Japanese Aerospace Co Inc | Stringer for aircraft |
| CN102796974A (en) * | 2012-08-13 | 2012-11-28 | 北京有色金属研究总院 | Improved 7000 series aluminum alloy double-stage overaging heat treatment technology |
| CN104195480A (en) * | 2014-09-08 | 2014-12-10 | 广西南南铝加工有限公司 | Integral aging method of Al-Zn-Mg alloy profile |
| CN104831203A (en) * | 2015-03-27 | 2015-08-12 | 广西南南铝加工有限公司 | High-speed rail train body Al-zinc-Mg alloy profile aging heat treatment method |
-
2015
- 2015-12-17 CN CN201510954534.2A patent/CN105385972B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4305763A (en) * | 1978-09-29 | 1981-12-15 | The Boeing Company | Method of producing an aluminum alloy product |
| JP2003277898A (en) * | 2002-03-27 | 2003-10-02 | Society Of Japanese Aerospace Co Inc | Stringer for aircraft |
| CN102796974A (en) * | 2012-08-13 | 2012-11-28 | 北京有色金属研究总院 | Improved 7000 series aluminum alloy double-stage overaging heat treatment technology |
| CN104195480A (en) * | 2014-09-08 | 2014-12-10 | 广西南南铝加工有限公司 | Integral aging method of Al-Zn-Mg alloy profile |
| CN104831203A (en) * | 2015-03-27 | 2015-08-12 | 广西南南铝加工有限公司 | High-speed rail train body Al-zinc-Mg alloy profile aging heat treatment method |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107937842A (en) * | 2017-12-01 | 2018-04-20 | 中南大学 | A kind of heat treatment method of Al Zn Mg Cu aluminium alloys |
| CN107937842B (en) * | 2017-12-01 | 2019-08-30 | 中南大学 | A kind of heat treatment method of Al-Zn-Mg-Cu aluminium alloy |
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| Publication number | Publication date |
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| CN105385972B (en) | 2017-09-26 |
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