7075 aluminum alloy plate creep age forming method

A creep aging forming and aluminum alloy sheet technology, which is applied in the field of creep aging forming to achieve the effect of eliminating residual stress, remarkable effect and simple operation.

Inactive Publication Date: 2015-03-11
CENT SOUTH UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0003] The purpose of the present invention is to provide a creep aging method suitable for the integral forming of 7075 aluminum alloy plates, which solves the bottleneck pro

Method used

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  • 7075 aluminum alloy plate creep age forming method
  • 7075 aluminum alloy plate creep age forming method
  • 7075 aluminum alloy plate creep age forming method

Examples

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Effect test

Embodiment 1

[0021] A 3mm thick plate is solution treated at 470°C for 1 hour and then water quenched, followed by 3% pre-deformation and artificial aging at 120°C for 24 hours. The return temperature is 185°C, the heating rate is 10°C / min, and the water quenching is carried out immediately after returning to the heat preservation for 20 minutes. A 3% pre-deformation is performed. The creep aging temperature is 120°C, the applied stress is 260MPa, and the forming time is 24 hours.

Embodiment 2

[0023] B 3mm thick plate is solution treated at 470°C for 1 hour, then water quenched, followed by 3% pre-deformation and artificial aging at 120°C for 24 hours. The return temperature is 185°C, the heating rate is 10°C / min, and the water quenching is carried out immediately after returning to the heat preservation for 40 minutes. A 3% pre-deformation is performed. The creep aging temperature is 120°C, the applied stress is 260MPa, and the forming time is 24 hours.

Embodiment 3

[0025] C 3mm thick plate is solution treated at 470°C for 1 hour, then water quenched, followed by 3% pre-deformation and artificial aging at 120°C for 24 hours. The return temperature is 185°C, the heating rate is 10°C / mm, and the water quenching is carried out immediately after returning to the heat preservation for 60 minutes. A 3% pre-deformation is performed. The creep aging temperature is 120°C, the applied stress is 260MPa, and the forming time is 24 hours.

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Abstract

The invention discloses a 7075 aluminum alloy plate creep age forming method. The method comprises the following steps: (1) carrying out solid-solution treatment on a 7075 aluminum alloy plate with a thickness of 2-40 mm for 30-90 minutes at a temperature of 466-480 DEG C, then water-quenching, subsequently carrying out 1-5 percent of pre-deformation and finally carrying out artificial aging treatment for 6-24 hours at a temperature of 80-120 DEG C; (2) carrying out retrogression treatment, wherein the retrogression treatment temperature is 160-200 DEG C, and the heat preservation time is 20-180 minutes, and then carrying out water quenching at a room temperature; (3) carrying out 1-5 percent of pre-deformation on the plate subjected to the retrogression treatment, then placing the plate in a mould and fixing; (4) carrying out creep age forming, wherein the creep age forming temperature is 120-160 DEG C, the applied stress is 200-260 MPa, and the forming time is 12-24 hours; (5) unloading the plate from the mould. When the method disclosed by the invention is utilized for processing the 7075 aluminum alloy plate, while the strength of the aluminum alloy plate is ensured, the corrosion resistance of the 7075 aluminum alloy plate can be effectively improved.

Description

technical field [0001] The invention relates to a creep aging forming method for a 7075 aluminum alloy plate, and belongs to the technical field of nonferrous metal material processing engineering. technical background [0002] 7075 aluminum alloy is a high-strength aluminum alloy that can be strengthened by heat treatment. It has the advantages of high strength / weight ratio, good hot workability and high fatigue toughness. It has become the key material of modern aerospace equipment and is widely used in aircraft Manufacture of wing panels and fuselage skins. In recent years, aircraft structural parts have been continuously developed in the direction of lightweight, long life, and high reliability, and their service performance has gradually become extreme. Therefore, high requirements are placed on forming technology. Integral panel manufacturing technology is a research hotspot in aerospace parts in recent years, and creep aging forming method is an ideal technology for ...

Claims

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Application Information

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IPC IPC(8): C22F1/053
CPCC22F1/053
Inventor 蔺永诚张金龙刘冠
Owner CENT SOUTH UNIV
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