CN110714147A - 6082 aluminum alloy plate for aviation and production process thereof - Google Patents
6082 aluminum alloy plate for aviation and production process thereof Download PDFInfo
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- CN110714147A CN110714147A CN201911068335.6A CN201911068335A CN110714147A CN 110714147 A CN110714147 A CN 110714147A CN 201911068335 A CN201911068335 A CN 201911068335A CN 110714147 A CN110714147 A CN 110714147A
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- 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
- C22C21/02—Alloys based on aluminium with silicon as the next major constituent
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- 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
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- 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
- C22C21/06—Alloys based on aluminium with magnesium as the next major constituent
- C22C21/08—Alloys based on aluminium with magnesium as the next major constituent with silicon
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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
- C22F1/05—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 of the Al-Si-Mg type, i.e. containing silicon and magnesium in approximately equal proportions
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Abstract
The invention relates to an aviation 6082 aluminum alloy plate and a production process thereof, wherein the aviation 6082 aluminum alloy plate comprises the following components in percentage by weight: 0.95 to 1.1 percent of Si, less than or equal to 0.4 percent of Fe, less than or equal to 0.05 percent of Cu, 0.65 to 0.75 percent of Mn, 0.95 to 1.1 percent of Mg, less than or equal to 0.1 percent of Cr, less than or equal to 0.1 percent of Zn, 0.02 to 0.03 percent of Ti, Al and other inevitable elements, less than or equal to 0.05 percent of other inevitable single elements, and less than or equal to 0.15 percent of the total; smelting and casting the elements in a smelting furnace to form an aluminum alloy ingot, then carrying out hot rolling at the temperature of more than or equal to 320 ℃, then carrying out cold rolling to the thickness of 0.9-1.0mm, and carrying out solution quenching on the aluminum alloy ingot in a continuous quenching line at the temperature of 500-520 ℃ and at the speed of 9-14 m/min; the aluminum alloy plate prepared by the process effectively improves the stamping forming performance of the aluminum alloy plate and realizes 180-degree bending of the aluminum alloy plate.
Description
Technical Field
The invention belongs to the technical field of aluminum alloy plate manufacturing, and particularly relates to an aviation 6082 aluminum alloy plate and a production process thereof.
Background
Aluminum alloy plates are a non-ferrous metal structural material which is most widely applied in industry, and are applied to various industries according to different materials, wherein 6082 alloy is widely applied to the field of aviation. However, most of the 6082 aluminum alloy plates applied to the aviation field are in a T6 state after solution heat treatment and aging, the strength of the state is high, the bending performance of the conventional 6082-T6 aluminum alloy plates is poor, if the aluminum alloy plates prepared by the traditional method are continuously subjected to stamping forming, the aluminum alloy plates are broken, and the stamping forming performance of the aluminum alloy plates is poor, so that the application of the 6082 aluminum alloy plates in the aviation field is influenced.
Disclosure of Invention
The invention aims to overcome the defects of the prior art and provide an aviation 6082 aluminum alloy plate which has good stamping forming performance and can realize 180-degree bending of the aluminum alloy plate on the premise of effectively meeting the strength performance of the aluminum alloy T4 state plate and a production process thereof.
The technical scheme of the invention is as follows:
a6082 aluminum alloy plate for aviation comprises the following components in percentage by weight: 0.95 to 1.1 percent of Si, less than or equal to 0.4 percent of Fe, less than or equal to 0.05 percent of Cu, 0.65 to 0.75 percent of Mn, 0.95 to 1.1 percent of Mg, less than or equal to 0.1 percent of Cr, less than or equal to 0.1 percent of Zn, 0.02 to 0.03 percent of Ti, Al and other inevitable elements, less than or equal to 0.05 percent of other inevitable single elements and less than or equal to 0.15 percent of total.
Further, the 6082 alloy plate for aviation comprises the following components in percentage by weight: 1.0% of Si, less than or equal to 0.4% of Fe, less than or equal to 0.05% of Cu, 0.7% of Mn, 1.0% of Mg, less than or equal to 0.1% of Cr, less than or equal to 0.1% of Zn, 0.025% of Ti, Al and other unavoidable elements, less than or equal to 0.05% of the other unavoidable individual elements, and less than or equal to 0.15% in total.
The production process of the 6082 aluminum alloy plate for aviation comprises the following preparation steps:
s1, weighing the above element ingredients according to the weight percentage, putting the elements into a smelting furnace, smelting at the temperature of 700 and 750 ℃, refining, degassing, slagging off and filtering, and then casting aluminum liquid into aluminum alloy ingots;
s2, uniformly carrying out thermalization treatment on the aluminum alloy ingot obtained in the step S1, cutting off the head and the tail, and milling the surface to obtain a pretreated alloy ingot;
s3, preheating the pretreated alloy ingot obtained in the step S2, and then hot-rolling the alloy ingot to a hot-rolled plate with the thickness of 5.0-6.0mm, wherein the final temperature of the hot rolling is more than or equal to 320 ℃;
s4, cold-rolling the hot-rolled plate obtained by the hot rolling in the step S3 to form an aluminum alloy sheet with the thickness of 0.9-1.0 mm;
s5, carrying out solution quenching on the aluminum alloy sheet obtained in the step S4 in a continuous quenching line at the temperature of 500 ℃ and 520 ℃ at the speed of 9-14 m/min;
s6, subjecting the aluminum alloy sheet after solution quenching to drawing and straightening plate shape to enable the unevenness of the strip to be less than or equal to 6I, and obtaining the aluminum alloy plate.
Further, in step S3, the hot rolling temperature is 320 ℃.
Further, in step S5, the solution quenching temperature of the continuous quenching line is 510 ℃ and the speed is 12 m/min.
Compared with the prior art, the invention has the beneficial effects that:
according to the invention, by optimizing the weight percentage of each metal element in the 6082 aluminum alloy plate for aviation, and changing the hot rolling thickness, the hot rolling final temperature, the cold rolling thickness and the temperature and speed of solution quenching, on the premise of ensuring that the tensile strength, the yield strength and the elongation rate meet the requirements, the stamping forming performance of the aluminum alloy plate is effectively improved, and 180-degree bending of the aluminum alloy plate is realized.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Example 1
A6082 aluminum alloy plate for aviation comprises the following components in percentage by weight: 0.9% of Si, less than or equal to 0.4% of Fe, less than or equal to 0.05% of Cu, 0.7% of Mn, 1.0% of Mg, less than or equal to 0.1% of Cr, less than or equal to 0.1% of Zn, 0.025% of Ti, Al and other unavoidable elements, less than or equal to 0.05% of the other unavoidable individual elements, and less than or equal to 0.15% in total.
The production process of the 6082 aluminum alloy plate for aviation comprises the following preparation steps:
s1, weighing the above element ingredients according to the weight percentage, putting the elements into a smelting furnace, smelting at the temperature of 700 and 750 ℃, refining, degassing, slagging off and filtering, and then casting aluminum liquid into aluminum alloy ingots;
s2, uniformly carrying out thermalization treatment on the aluminum alloy ingot obtained in the step S1, cutting off the head and the tail, and milling the surface to obtain a pretreated alloy ingot;
s3, preheating the pretreated alloy ingot obtained in the step S2, and then hot-rolling the alloy ingot to a hot-rolled plate with the thickness of 5.5mm, wherein the final hot-rolling temperature is more than or equal to 320 ℃;
s4, cold-rolling the hot-rolled plate obtained by the hot rolling in the step S3 to form an aluminum alloy sheet with the thickness of 0.95 mm;
s5, carrying out solution quenching on the aluminum alloy sheet obtained in the step S4 in a continuous quenching line at the temperature of 500 ℃ and 520 ℃ at the speed of 12 m/min;
s6, subjecting the aluminum alloy sheet after solution quenching to drawing and straightening plate shape to enable the unevenness of the strip to be less than or equal to 6I, and obtaining the aluminum alloy plate.
Example 2
A6082 aluminum alloy plate for aviation comprises the following components in percentage by weight: 1.1% of Si, less than or equal to 0.4% of Fe, less than or equal to 0.05% of Cu, 0.65% of Mn, 0.95% of Mg, less than or equal to 0.1% of Cr, less than or equal to 0.1% of Zn, 0.03% of Ti, Al and other inevitable elements, less than or equal to 0.05% of other inevitable single elements, and less than or equal to 0.15% in total.
The production process of the 6082 aluminum alloy plate for aviation comprises the following preparation steps:
s1, weighing the above element ingredients according to the weight percentage, putting the elements into a smelting furnace, smelting at the temperature of 700 and 750 ℃, refining, degassing, slagging off and filtering, and then casting aluminum liquid into aluminum alloy ingots;
s2, uniformly carrying out thermalization treatment on the aluminum alloy ingot obtained in the step S1, cutting off the head and the tail, and milling the surface to obtain a pretreated alloy ingot;
s3, preheating the pretreated alloy ingot obtained in the step S2, and then hot-rolling the alloy ingot to a hot-rolled plate with the thickness of 5.0mm, wherein the final hot-rolling temperature is more than or equal to 320 ℃;
s4, cold-rolling the hot-rolled plate obtained by the hot rolling in the step S3 to form an aluminum alloy sheet with the thickness of 0.9 mm;
s5, carrying out solution quenching on the aluminum alloy sheet obtained in the step S4 in a continuous quenching line at the temperature of 510 ℃ at the speed of 10 m/min;
s6, subjecting the aluminum alloy sheet after solution quenching to drawing and straightening plate shape to enable the unevenness of the strip to be less than or equal to 6I, and obtaining the aluminum alloy plate.
Example 3
A6082 aluminum alloy plate for aviation comprises the following components in percentage by weight: 0.95% of Si, less than or equal to 0.4% of Fe, less than or equal to 0.05% of Cu, 0.75% of Mn, 1.1% of Mg, less than or equal to 0.1% of Cr, less than or equal to 0.1% of Zn, 0.02% of Ti, Al and other inevitable elements, less than or equal to 0.05% of other inevitable single elements, and less than or equal to 0.15% in total.
The production process of the 6082 aluminum alloy plate for aviation comprises the following preparation steps:
s1, weighing the above element ingredients according to the weight percentage, putting the elements into a smelting furnace, smelting at the temperature of 700 and 750 ℃, refining, degassing, slagging off and filtering, and then casting aluminum liquid into aluminum alloy ingots;
s2, uniformly carrying out thermalization treatment on the aluminum alloy ingot obtained in the step S1, cutting off the head and the tail, and milling the surface to obtain a pretreated alloy ingot;
s3, preheating the pretreated alloy ingot obtained in the step S2, and then hot-rolling the alloy ingot to a hot-rolled plate with the thickness of 6.0mm, wherein the final hot-rolling temperature is more than or equal to 320 ℃;
s4, cold-rolling the hot-rolled plate obtained by the hot rolling in the step S3 to form an aluminum alloy sheet with the thickness of 1.0 mm;
s5, carrying out solution quenching on the aluminum alloy sheet obtained in the step S4 in a continuous quenching line at the temperature of 520 ℃ at the speed of 14 m/min;
s6, subjecting the aluminum alloy sheet after solution quenching to drawing and straightening plate shape to enable the unevenness of the strip to be less than or equal to 6I, and obtaining the aluminum alloy plate.
The experimental process comprises the following steps:
preparing aluminum alloy plates according to the examples 1 to 3 respectively, and measuring the performance of the aluminum alloy plates; the specific measurement results are shown in the following table:
according to the experimental results on the performance of the aluminum alloy plates prepared in the foregoing embodiments 1-3, it can be seen that the tensile strength of the aluminum alloy plate obtained by the material for preparing aluminum alloy and the production process provided by the present invention is between 205 and 240, the yield strength is not less than 110, the elongation is not less than 18%, and the performance of the aluminum alloy plate is still good after the aluminum alloy plate is bent at 180 °. The performance requirements of the aluminum alloy plate are met, and meanwhile, the stamping forming performance and the bending performance of the aluminum alloy plate are effectively improved.
Although the present invention has been described in detail with reference to the foregoing embodiments, it will be apparent to those skilled in the art that various changes in the embodiments and/or modifications of the invention can be made, and equivalents and modifications of some features of the invention can be made without departing from the spirit and scope of the invention.
Claims (5)
1. The 6082 aluminum alloy plate for aviation is characterized by comprising the following components in percentage by weight: 0.95 to 1.1 percent of Si, less than or equal to 0.4 percent of Fe, less than or equal to 0.05 percent of Cu, 0.65 to 0.75 percent of Mn, 0.95 to 1.1 percent of Mg, less than or equal to 0.1 percent of Cr, less than or equal to 0.1 percent of Zn, 0.02 to 0.03 percent of Ti, Al and other inevitable elements, wherein the total content of the other inevitable elements is less than or equal to 0.05 percent and less than or equal to 0.15 percent.
2. The 6082 alloy plate for the aviation as claimed in claim 1, wherein the 6082 alloy plate comprises the following components in percentage by weight: 1.0% of Si, less than or equal to 0.4% of Fe, less than or equal to 0.05% of Cu, 0.7% of Mn, 1.0% of Mg, less than or equal to 0.1% of Cr, less than or equal to 0.1% of Zn, 0.025% of Ti, Al and other unavoidable elements, less than or equal to 0.05% of the other unavoidable individual elements, and less than or equal to 0.15% in total.
3. Process for the production of 6082 aluminium alloy plates for aviation according to any of the claims from 1 to 2, characterized by comprising the following preparation steps:
s1, weighing the above element ingredients according to the weight percentage, putting the elements into a smelting furnace, smelting at the temperature of 700 and 750 ℃, refining, degassing, slagging off and filtering, and then casting aluminum liquid into aluminum alloy ingots;
s2, uniformly carrying out thermalization treatment on the aluminum alloy ingot obtained in the step S1, cutting off the head and the tail, and milling the surface to obtain a pretreated alloy ingot;
s3, preheating the pretreated alloy ingot obtained in the step S2, and then hot-rolling the alloy ingot to a hot-rolled plate with the thickness of 5.0-6.0mm, wherein the final temperature of the hot rolling is more than or equal to 320 ℃;
s4, cold-rolling the hot-rolled plate obtained by the hot rolling in the step S3 to form an aluminum alloy sheet with the thickness of 0.9-1.0 mm;
s5, carrying out solution quenching on the aluminum alloy sheet obtained in the step S4 in a continuous quenching line at the temperature of 500 ℃ and 520 ℃ at the speed of 9-14 m/min;
s6, subjecting the aluminum alloy sheet after solution quenching to drawing and straightening plate shape to enable the unevenness of the strip to be less than or equal to 6I, and obtaining the aluminum alloy plate.
4. The production process of the 6082 aluminum alloy plate for aviation as claimed in claim 3, wherein: in step S3, the hot rolling temperature is 320 ℃.
5. The production process of the 6082 aluminum alloy plate for aviation as claimed in claim 3, wherein: in step S5, the solution quenching temperature of the continuous quenching line is 510 ℃ and the speed is 12 m/min.
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN111471902A (en) * | 2020-05-22 | 2020-07-31 | 天津忠旺铝业有限公司 | Processing method of 6082 aluminum alloy plate for high-performance rail transit |
| CN113186433A (en) * | 2021-03-24 | 2021-07-30 | 辽宁忠旺集团有限公司 | 6082 aluminum alloy and process for casting to replace deformed extrusion rod by using same |
| CN113355566A (en) * | 2021-04-20 | 2021-09-07 | 山东国泰铝业有限公司 | Aluminum alloy material for engineering and preparation method thereof |
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| CN113186433A (en) * | 2021-03-24 | 2021-07-30 | 辽宁忠旺集团有限公司 | 6082 aluminum alloy and process for casting to replace deformed extrusion rod by using same |
| CN113355566A (en) * | 2021-04-20 | 2021-09-07 | 山东国泰铝业有限公司 | Aluminum alloy material for engineering and preparation method thereof |
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| CN110714147B (en) | 2021-06-01 |
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Effective date of registration: 20220701 Address after: No. 162, Jinbai Road, Zhengzhou high tech Industrial Development Zone, Zhengzhou, Henan 450001 Patentee after: Henan Mingsheng New Material Technology Co.,Ltd. Address before: 450001 No.6, Changchun Road, high tech Development Zone, Zhengzhou City, Henan Province Patentee before: Zhengzhou Mingtai Industrial Co.,Ltd. |
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