Preparation method of online continuous solution heat treatment Al-Zn-Mg-Cu aluminum alloy T6-state aluminum-clad sheet for aviation
A multi-stage homogenization and high-temperature rolling process for Al-Zn-Mg-Cu aluminum alloy sheets addresses performance gaps by enhancing tensile and yield strengths, achieving higher mechanical properties through controlled online continuous solution heat treatment.
Patent Information
- Application Number
- CN202411382496.3
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2024-09-30
- Publication Date
- 2025-01-03
AI Technical Summary
The existing methods for preparing Al-Zn-Mg-Cu aluminum alloy T6 state aluminum clad sheets for large passenger aircraft fuselage keel beams do not meet the stringent requirements for light weight, low energy consumption, and high performance, particularly in terms of tensile and yield strength, due to insufficient homogenization and online continuous solid solution heat treatment processes.
A multi-stage homogenization and high-temperature rolling process followed by online continuous solution heat treatment, including steps such as ingot preparation, welding, hot and cold rolling, and controlled quenching, to achieve enhanced mechanical properties.
The method results in Al-Zn-Mg-Cu aluminum alloy T6 sheets with improved tensile and yield strengths, meeting or exceeding industry standards, and ensuring stable performance through controlled dissolution of phases during heat treatment.
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Figure CN119243062A_ABST
Abstract
Description
Technical Field
[0001] The invention belongs to the technical field of aluminum alloy clad aluminum sheet processing, and specifically relates to a method for preparing an aviation-use online continuous solid solution heat treatment Al-Zn-Mg-Cu aluminum alloy T6 state clad aluminum sheet. Background Art
[0002] Under the new situation that countries around the world attach great importance to the cultivation and development of strategic emerging industries, the development of the aviation industry is facing huge opportunities and challenges. One of the characteristics of strategic emerging industries is "green", mainly "environmentally friendly" and "green" industries with low energy consumption, low emissions and renewable energy, which puts forward more stringent requirements for the technological innovation of the aviation manufacturing industry. By optimizing the structural design of the aircraft model, the effects of light weight, low energy consumption and low emissions can be achieved, and higher requirements are also put forward for the selection of aluminum alloys. At present, relevant work has been carried out on aviation aluminum alloy sheets, but the Al-Zn-Mg-Cu aluminum alloy T6 state aluminum clad sheet for the keel beam of the fuselage of large passenger aircraft has not yet been carried out in accordance with the model design and airworthiness requirements. Related basic research and application evaluation work. Through the development of new industrial preparation technology, the homogenization process of industrialized Al-Zn-Mg-Cu aluminum alloy T6 state aluminum clad sheet, cold rolling deformation, online continuous solution heat treatment and coordinated control of organization and performance are solved, and the product quality of Al-Zn-Mg-Cu aluminum alloy T6 state aluminum clad sheet for large passenger aircraft is improved. Summary of the invention
[0003] The purpose of the present invention is to solve the above technical problems and to provide a method for preparing Al-Zn-Mg-Cu aluminum alloy T6 aluminum-clad thin plate for aviation use by online continuous solid solution heat treatment.
[0004] A method for preparing an Al-Zn-Mg-Cu aluminum alloy T6 aluminum-clad sheet for aviation by online continuous solution heat treatment, which is carried out in the following steps:
[0005] 1. The Al-Zn-Mg-Cu aluminum alloy ingot is homogenized, then milled and sawed to obtain the ingot core material, and then double-sided 7072 alloy aluminum plates of equal thickness are welded to obtain the welded Al-Zn-Mg-Cu aluminum alloy composite ingot;
[0006] 2. The Al-Zn-Mg-Cu aluminum alloy composite ingot after welding is heated to 460° C. to 470° C. and kept warm for 2 h to 18 h, and then roughly hot rolled at a low speed to a thickness of 100 mm to 200 mm, and then roughly hot rolled at a high speed to a thickness of 20 mm to 24 mm, and finally hot finished rolled to a thickness of 4.0 mm to 7.8 mm to obtain an Al-Zn-Mg-Cu aluminum alloy hot finished rolled coil blank;
[0007] 3. The Al-Zn-Mg-Cu aluminum alloy hot-rolled coil blank is cold-rolled, and the total cold-rolling deformation is controlled at 40% to 68% to obtain an Al-Zn-Mg-Cu aluminum alloy cold-rolled coil blank, and then both end faces are trimmed and the surface is cleaned to obtain an Al-Zn-Mg-Cu aluminum alloy cold-rolled coil;
[0008] 4. The Al-Zn-Mg-Cu aluminum alloy cold-rolled coil is subjected to online continuous solution heat treatment, the solution temperature is carried out in accordance with the AMS 2772 standard, the process speed is 7m / min to 11m / min, and the Al-Zn-Mg-Cu aluminum alloy quenched coil is obtained, and then the coil is unrolled and sliced to obtain the Al-Zn-Mg-Cu aluminum alloy quenched thin plate;
[0009] 5. After quenching, the Al-Zn-Mg-Cu aluminum alloy thin plate is artificially aged at a temperature of 116°C to 126°C for a holding time of 23h to 25h to obtain an Al-Zn-Mg-Cu aluminum alloy T6 aluminum-clad thin plate, thereby completing the preparation method.
[0010] Furthermore, in the homogenization treatment described in step 1, the Al-Zn-Mg-Cu aluminum alloy ingot is heated to 465°C-475°C and kept warm for 16h-24h, and after the insulation is completed, the temperature is further raised to 475°C-485°C and kept warm for 20h-24h.
[0011] Furthermore, the specification of the ingot core material in step one is 475mm~495mm×1580mm~1600mm×4400mm~4600mm.
[0012] Furthermore, the thickness of the 7072 alloy aluminum-clad plate in step 1 is 15 mm to 18 mm.
[0013] Furthermore, the low-speed hot rough rolling in step 2 has a speed of 0.4 m / s to 1.0 m / s.
[0014] Furthermore, the high-speed hot rough rolling in step 2 has a speed of 1.0 m / s to 3.0 m / s.
[0015] Furthermore, the hot finishing rolling in step 2 is carried out at a temperature of 300°C to 350°C.
[0016] Furthermore, the thickness of the Al-Zn-Mg-Cu aluminum alloy cold-rolled coil blank in step three is 1.6 mm to 3.25 mm.
[0017] Advantages of the present invention:
[0018] 1. The present invention has developed a method for preparing an online continuous solid solution heat treatment Al-Zn-Mg-Cu aluminum alloy T6 aluminum clad sheet for aviation use, which adopts a multi-stage homogenization and high-temperature rolling production method to achieve short-time online continuous solid solution heat treatment production. Its T6 state tensile strength can reach 529MPa~545MPa, which is 20MPa~30MPa higher than the product standard requirements, and its yield strength can reach 467MPa~486MPa, which is 25MPa~45MPa higher than the product standard requirements. The present invention solves the problem that the performance does not meet the index requirements due to insufficient insulation time of online continuous solid solution heat treatment, breaks through the industrial preparation technology of Al-Zn-Mg-Cu aluminum alloy T6 aluminum clad sheet for large civil aircraft, and provides a new optional material for high-strength damage-tolerant T6 aluminum clad sheet for the web of the fuselage keel beam of large passenger aircraft.
[0019] 2. K of the Al-Zn-Mg-Cu aluminum alloy T6 aluminum-clad sheet prepared by the present invention app The value can reach 60MPa·m 1 / 2 ~80MPa·m 1 / 2 , strength variation coefficient C v Between 0.85% and 1.5%, the product performance stability is relatively good.
[0020] 3. The present invention develops a method for preparing Al-Zn-Mg-Cu aluminum alloy T6 aluminum-clad thin plates for aviation use. Through online continuous solution heat treatment process speed control, the quenching transfer time of the thin plates meets the requirements of the AMS2772 standard, that is, it ensures that the dissolvable phase has enough time to dissolve when the thin plates pass through the heating furnace zone, and prevents the thin plates from desolvation due to excessively long quenching transfer time, which affects the strength of the thin plates and intergranular corrosion performance.
[0021] The invention is suitable for preparing Al-Zn-Mg-Cu aluminum alloy T6 state aluminum clad thin plates for aviation by online continuous solid solution heat treatment. BRIEF DESCRIPTION OF THE DRAWINGS
[0022] Figure 1 This is a physical picture of the Al-Zn-Mg-Cu aluminum alloy T6 aluminum-clad thin plate for aviation prepared in the example;
[0023] Figure 2 This is the EBSD organization diagram of the Al-Zn-Mg-Cu aluminum alloy T6 aluminum-clad thin plate for aviation prepared in the example;
[0024] Figure 3 This is a SEM image of the online continuous solution heat treated Al-Zn-Mg-Cu aluminum alloy T6 aluminum clad sheet for aviation use prepared in the example. DETAILED DESCRIPTION
[0025] The technical solution of the present invention is not limited to the specific implementation modes listed below, but also includes any combination of the specific implementation modes.
[0026] Specific implementation method 1: This implementation method is a method for preparing an online continuous solution heat treatment Al-Zn-Mg-Cu aluminum alloy T6 aluminum clad sheet for aviation, which is carried out in the following steps:
[0027] 1. The Al-Zn-Mg-Cu aluminum alloy ingot is homogenized, then milled and sawed to obtain the ingot core material, and then double-sided 7072 alloy aluminum plates of equal thickness are welded to obtain the welded Al-Zn-Mg-Cu aluminum alloy composite ingot;
[0028] 2. The Al-Zn-Mg-Cu aluminum alloy composite ingot after welding is heated to 460° C. to 470° C. and kept warm for 2 h to 18 h, and then roughly hot rolled at a low speed to a thickness of 100 mm to 200 mm, and then roughly hot rolled at a high speed to a thickness of 20 mm to 24 mm, and finally hot finished rolled to a thickness of 4.0 mm to 7.8 mm to obtain an Al-Zn-Mg-Cu aluminum alloy hot finished rolled coil blank;
[0029] 3. The Al-Zn-Mg-Cu aluminum alloy hot-rolled coil blank is cold-rolled, and the total cold-rolling deformation is controlled at 40% to 68% to obtain an Al-Zn-Mg-Cu aluminum alloy cold-rolled coil blank, and then both end faces are trimmed and the surface is cleaned to obtain an Al-Zn-Mg-Cu aluminum alloy cold-rolled coil;
[0030] 4. The Al-Zn-Mg-Cu aluminum alloy cold-rolled coil is subjected to online continuous solution heat treatment, the solution temperature is carried out in accordance with the AMS 2772 standard, the process speed is 7m / min to 11m / min, and the Al-Zn-Mg-Cu aluminum alloy quenched coil is obtained, and then the coil is unrolled and sliced to obtain the Al-Zn-Mg-Cu aluminum alloy quenched thin plate;
[0031] 5. After quenching, the Al-Zn-Mg-Cu aluminum alloy thin plate is artificially aged at a temperature of 116°C to 126°C for a holding time of 23h to 25h to obtain an Al-Zn-Mg-Cu aluminum alloy T6 aluminum-clad thin plate, thereby completing the preparation method.
[0032] Specific embodiment 2: This embodiment is different from specific embodiment 1 in that, in step 1, the homogenization treatment is as follows: the Al-Zn-Mg-Cu aluminum alloy ingot is heated to 465°C to 475°C and kept warm for 16h to 24h, and then the temperature is further raised to 475°C to 485°C and kept warm for 20h to 24h. The other steps and parameters are the same as those in specific embodiment 1.
[0033] Specific implementation method 3: This implementation method is different from specific implementation method 1 in that the specification of the ingot core material in step 1 is 475mm-495mm×1580mm-1600mm×4400mm-4600mm. Other steps and parameters are the same as those in specific implementation method 1.
[0034] Specific implementation method 4: This implementation method is different from specific implementation method 1 in that the thickness of the 7072 alloy aluminum-clad plate in step 1 is 15 mm to 18 mm. Other steps and parameters are the same as those in specific implementation method 1.
[0035] Specific implementation method 5: This implementation method is different from the specific implementation method 1 in that the low-speed hot rough rolling in step 2 has a speed of 0.4 m / s to 1.0 m / s. The other steps and parameters are the same as those in the specific implementation method 1.
[0036] Specific implementation method 6: This implementation method is different from the specific implementation method 1 in that the high-speed hot rough rolling in step 2 has a speed of 1.0 m / s to 3.0 m / s. The other steps and parameters are the same as those in the specific implementation method 1.
[0037] Specific embodiment 7: This embodiment is different from the specific embodiment 1 in that the hot finishing rolling in step 2 is performed at a temperature of 300° C. to 350° C. The other steps and parameters are the same as those in the specific embodiment 1.
[0038] Specific embodiment 8: This embodiment is different from specific embodiment 1 in that the thickness of the Al-Zn-Mg-Cu aluminum alloy cold-rolled coil blank in step 3 is 1.6 mm to 3.25 mm. Other steps and parameters are the same as those in specific embodiment 1.
[0039] Specific embodiment 9: This embodiment is different from specific embodiment 1 in that the process speed in step 4 is 8 m / min to 10 m / min. The other steps and parameters are the same as those in specific embodiment 1.
[0040] Specific embodiment 10: This embodiment is different from specific embodiment 1 in that the aging temperature in step 5 is 120° C. and the holding time is 24 hours. The other steps and parameters are the same as those in specific embodiment 1.
[0041] The beneficial effects of the present invention are verified by the following examples:
[0042] Example:
[0043] A method for preparing an Al-Zn-Mg-Cu aluminum alloy T6 aluminum-clad sheet for aviation by online continuous solution heat treatment, which is carried out in the following steps:
[0044] 1. The Al-Zn-Mg-Cu aluminum alloy ingot is homogenized, then milled and sawed to obtain the ingot core material, and then double-sided 7072 alloy aluminum plates of equal thickness are welded to obtain the welded Al-Zn-Mg-Cu aluminum alloy composite ingot;
[0045] 2. The Al-Zn-Mg-Cu aluminum alloy composite ingot after welding is heated to 460°C-470°C and kept warm for 4 hours, and then hot rough rolled at a low speed to a thickness of 200 mm, and then hot rough rolled at a high speed to a thickness of 24 mm, and finally hot finish rolled to a thickness of 4.0 mm to obtain an Al-Zn-Mg-Cu aluminum alloy hot finish rolled coil blank;
[0046] 3. The Al-Zn-Mg-Cu aluminum alloy hot-rolled coil blank is cold-rolled, and the total cold-rolling deformation is controlled at 60% to obtain an Al-Zn-Mg-Cu aluminum alloy cold-rolled coil blank, and then both end faces are trimmed and the surface is cleaned to obtain an Al-Zn-Mg-Cu aluminum alloy cold-rolled coil;
[0047] 4. The Al-Zn-Mg-Cu aluminum alloy cold-rolled coil is subjected to online continuous solution heat treatment, the solution temperature is carried out in accordance with the AMS 2772 standard, the process speed is 8m / min to 10m / min, and the Al-Zn-Mg-Cu aluminum alloy quenched coil is obtained, and then the coil is unrolled and sliced to obtain the Al-Zn-Mg-Cu aluminum alloy quenched thin plate;
[0048] 5. After quenching, the Al-Zn-Mg-Cu aluminum alloy thin plate is artificially aged at a temperature of 120° C. for 24 h to obtain an Al-Zn-Mg-Cu aluminum alloy T6 aluminum-clad thin plate, thus completing the preparation method.
[0049] The homogenization treatment in step 1 of this embodiment is as follows: the Al-Zn-Mg-Cu aluminum alloy ingot is heated to 470° C. and kept at this temperature for 20 hours, and then the temperature is further raised to 480° C. and kept at this temperature for 24 hours.
[0050] The specifications of the ingot core material described in step 1 of this embodiment are 480mm×1600mm×4600mmm.
[0051] The thickness of the 7072 alloy aluminum-clad plate described in step 1 of this embodiment is 16 mm.
[0052] The low-speed hot rough rolling described in step 2 of this embodiment has a speed of 0.5 to 0.7 m / s.
[0053] The high-speed hot rough rolling in step 2 of this embodiment has a speed of 1.0 to 3.0 m / s.
[0054] The hot finishing rolling in step 2 of this embodiment has a temperature of 300°C to 350°C.
[0055] The thickness of the Al-Zn-Mg-Cu aluminum alloy cold-rolled coil blank described in step three of this embodiment is 1.6 mm.
[0056] The Al-Zn-Mg-Cu aluminum alloy T6 aluminum-clad sheet obtained in this embodiment for aviation is as follows: Figure 1 As shown, the surface quality of the thin plate is improved; the preparation method in this embodiment improves production efficiency and provides a guarantee for product promotion and stable production.
[0057] The EBSD structure diagram of the Al-Zn-Mg-Cu aluminum alloy T6 aluminum-clad thin plate obtained in this embodiment for aviation online continuous solution heat treatment (see Figure 2 ), it can be seen that its grains are completely recrystallized and the average grain size is 15.1μm, ensuring it has good plasticity.
[0058] The SEM microstructure of the Al-Zn-Mg-Cu aluminum alloy T6 aluminum-clad sheet obtained in this embodiment for aviation on-line continuous solution heat treatment (see Figure 3 ), it can be seen that the strengthening phase in the organization is almost completely dissolved back into the matrix, providing a basis for the subsequent aging precipitation strengthening of the thin plate.
[0059] The online continuous solution heat treatment Al-Zn-Mg-Cu aluminum alloy T6 state aluminum clad thin plate for aviation obtained in this embodiment has a T6 state tensile strength of 529MPa-545MPa, which is 20MPa-30MPa higher than the product standard requirement, and a yield strength of 467MPa-486MPa, which is 25MPa-45MPa higher than the product standard requirement.
[0060] The Al-Zn-Mg-Cu aluminum alloy T6 aluminum-clad sheet obtained in this embodiment for aviation use has a K app The value can reach 60MPa·m 1 / 2 ~80MPa·m 1 / 2 , strength variation coefficient C v Between 0.85% and 1.5%, the product performance stability is relatively good.
[0061] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Although the present invention has been described in detail with reference to the aforementioned embodiments, it is still possible for those skilled in the art to modify the technical solutions described in the aforementioned embodiments, or to make equivalent substitutions for some of the technical features therein. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the protection scope of the present invention.
Claims
1. A method for preparing an online continuous solution heat treatment Al-Zn-Mg-Cu aluminum alloy T6 aluminum clad sheet for aviation, characterized in that It proceeds as follows:
1. The Al-Zn-Mg-Cu aluminum alloy ingot is homogenized, then milled and sawed to obtain the ingot core material, and then double-sided 7072 alloy aluminum plates of equal thickness are welded to obtain the welded Al-Zn-Mg-Cu aluminum alloy composite ingot; 2. The Al-Zn-Mg-Cu aluminum alloy composite ingot after welding is heated to 460° C. to 470° C. and kept warm for 2 h to 18 h, and then roughly hot rolled at a low speed to a thickness of 100 mm to 200 mm, and then roughly hot rolled at a high speed to a thickness of 20 mm to 24 mm, and finally hot finished rolled to a thickness of 4.0 mm to 7.8 mm to obtain an Al-Zn-Mg-Cu aluminum alloy hot finished rolled coil blank; 3. The Al-Zn-Mg-Cu aluminum alloy hot-rolled coil blank is cold-rolled, and the total cold-rolling deformation is controlled at 40% to 68% to obtain an Al-Zn-Mg-Cu aluminum alloy cold-rolled coil blank, and then both end faces are trimmed and the surface is cleaned to obtain an Al-Zn-Mg-Cu aluminum alloy cold-rolled coil; 4. The Al-Zn-Mg-Cu aluminum alloy cold-rolled coil is subjected to online continuous solution heat treatment, the solution temperature is carried out in accordance with the AMS2772 standard, the process speed is 7m / min to 11m / min, and the Al-Zn-Mg-Cu aluminum alloy quenched coil is obtained, and then the coil is unrolled and sliced to obtain the Al-Zn-Mg-Cu aluminum alloy quenched thin plate; 5. After quenching, the Al-Zn-Mg-Cu aluminum alloy thin plate is artificially aged at a temperature of 116°C to 126°C for a holding time of 23h to 25h to obtain an Al-Zn-Mg-Cu aluminum alloy T6 aluminum-clad thin plate, thereby completing the preparation method.
2. The method for preparing an online continuous solution heat treatment Al-Zn-Mg-Cu aluminum alloy T6 aluminum clad sheet for aviation use according to claim 1, characterized in that The homogenization treatment in step 1 is as follows: the Al-Zn-Mg-Cu aluminum alloy ingot is heated to 465°C-475°C and kept warm for 16h-24h, and then the temperature is further raised to 475°C-485°C and kept warm for 20h-24h.
3. The method for preparing an online continuous solution heat treated Al-Zn-Mg-Cu aluminum alloy T6 aluminum clad sheet for aviation use according to claim 1, characterized in that The specification of the ingot core material described in step 1 is 475mm~495mm×1580mm~1600mm×4400mm~4600mm.
4. The method for preparing an online continuous solution heat treatment Al-Zn-Mg-Cu aluminum alloy T6 aluminum clad sheet for aviation use according to claim 1, characterized in that The thickness of the 7072 alloy aluminum-clad plate in step 1 is 15 mm to 18 mm.
5. The method for preparing an online continuous solution heat treated Al-Zn-Mg-Cu aluminum alloy T6 aluminum clad sheet for aviation use according to claim 1, characterized in that The low-speed hot rough rolling in step 2: the speed is 0.4m / s to 1.0m / s, and the temperature is 430°C to 470°C.
6. The method for preparing an online continuous solution heat treatment Al-Zn-Mg-Cu aluminum alloy T6 aluminum clad sheet for aviation use according to claim 1, characterized in that The high-speed hot rough rolling in step 2 has a speed of 1.0 m / s to 3.0 m / s.
7. The method for preparing an online continuous solution heat treated Al-Zn-Mg-Cu aluminum alloy T6 aluminum clad sheet for aviation use according to claim 1, characterized in that The hot finishing rolling in step 2 is at 300°C to 350°C.
8. The method for preparing an online continuous solid solution heat treatment Al-Zn-Mg-Cu aluminum alloy T6 aluminum clad sheet for aviation use according to claim 1, characterized in that The thickness of the Al-Zn-Mg-Cu aluminum alloy cold-rolled coil blank in step three is 1.6 mm to 3.25 mm.
9. The method for preparing an online continuous solution heat treated Al-Zn-Mg-Cu aluminum alloy T6 aluminum clad sheet for aviation use according to claim 1, characterized in that The process speed in step 4 is 8m / min to 10m / min.
10. The method for preparing an online continuous solution heat treated Al-Zn-Mg-Cu aluminum alloy T6 aluminum clad sheet for aviation use according to claim 1, characterized in that The aging temperature in step 5 is 120° C. and the insulation time is 24 hours.