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Heat treatment method for machining deformation prevention of 7055 aluminium alloy thin-walled structure

A heat treatment method and thin-walled structure technology, which is applied in the field of aviation material processing, can solve the problems of large residual stress, cracking and scrapping of components, and low processing accuracy, and achieve the effect of improving dimensional accuracy and preventing processing deformation

Inactive Publication Date: 2017-02-15
CHINA HELICOPTER RES & DEV INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] The thin-walled structure of 7055 aluminum alloy is prone to large deformation during the machining process. Severe deformation will lead to low machining accuracy and even cracking and scrapping
At present, after the 7055 aluminum alloy thin-walled structure is machined and undergoes primary or secondary aging, the component still has a large residual stress and is easily deformed.

Method used

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  • Heat treatment method for machining deformation prevention of 7055 aluminium alloy thin-walled structure

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0053] Embodiment 1: The 7055 aluminum alloy forging blank is roughly machined to a sufficient margin, and after T74 heat treatment, three times of machining and three stages of aging treatment are carried out, and the steps are as follows:

[0054] a. After T74 treatment, the components are rough-machined to a certain margin of 5mm, and then undergo primary aging treatment. Temperature: 180°C, keep warm for 30 hours.

[0055] b. After the primary aging, the component is reprocessed to a certain margin of 1mm, and then the secondary aging treatment is carried out. Temperature: 200°C, keep warm for 28 hours.

[0056] c. After the secondary aging, the component is reprocessed to a certain margin of 0.5mm, and then the tertiary aging treatment is carried out. Temperature: 150°C, keep warm for 25 hours.

[0057] d. After the three-stage aging, the components are subjected to multiple finishing processes 3 times to the finished product.

Embodiment 2

[0058] Embodiment 2: The 7055 aluminum alloy forging blank is roughly machined to a sufficient margin, and after T74 heat treatment, three times of machining and three stages of aging treatment are carried out, and the steps are as follows:

[0059] a. After T74 treatment, the component is rough machined to a certain margin of 8mm, and then the primary aging treatment is performed. Temperature: 200°C, keep warm for 30 hours.

[0060] b. After the primary aging, the component is reprocessed to a certain margin of 3mm, and then the secondary aging treatment is carried out. Temperature: 190°C, keep warm for 28 hours.

[0061] c. After the secondary aging, the component is reprocessed to a certain margin of 1mm, and then the tertiary aging treatment is carried out. Temperature: 170°C, keep warm for 25 hours.

[0062] d. After the three-stage aging, the components are subjected to multiple finishing processes 3 times to the finished product.

Embodiment 3

[0063]Embodiment 3: The 7055 aluminum alloy forging blank is roughly machined to a sufficient margin. After T74 heat treatment, three times of machining and three stages of aging treatment are carried out. The steps are as follows:

[0064] a. After T74 treatment, the component is rough-machined to a certain margin of 6mm, and then undergoes primary aging treatment. Temperature: 180°C, keep warm for 30 hours.

[0065] b. After the primary aging, the component is reprocessed to a certain margin of 2mm, and then the secondary aging treatment is carried out. Temperature: 200°C, keep warm for 28 hours.

[0066] c. After the secondary aging, the component is reprocessed to a certain margin of 0.8mm, and then the tertiary aging treatment is carried out. Temperature: 150°C, keep warm for 25 hours.

[0067] d. After the three-stage aging, the components are subjected to multiple finishing processes 5 times to the finished product.

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Abstract

The invention provides a heat treatment method for machining deformation prevention of a 7055 aluminium alloy thin-walled structure. The heat treatment method comprises the following steps: performing rough machining on a member blank till the thickness allowance is 5-8 mm; performing first-level aging treatment; re-performing rough machining on the blank subjected to first-level aging treatment till the thickness allowance is 1-3 mm; performing second-level aging treatment; re-performing rough machining on the blank subjected to second-level aging treatment till the thickness allowance is 0.5-1 mm; performing third-level aging treatment; and finally, performing finish machining on the blank subjected to third-level aging treatment into an end product, wherein the temperatures of the first-level, second-level and third-level aging treatment are 150-250 DEG C and maintained for 25-35 h. The three-level of aging treatment can reduce the residual stress of the 7055 aluminium alloy thin-walled structure after each time of machining, further can prevent the 7055 aluminium alloy thin-walled structure from machining deformation in the machining process, improves the product dimensional accuracy and ensures that a product can maintain the original strength level.

Description

technical field [0001] The invention belongs to the field of aviation material processing, and in particular relates to a heat treatment method for preventing processing deformation of a 7055 aluminum alloy thin-walled structure. Background technique [0002] 7055 aluminum alloy is currently the alloy with the best comprehensive performance in the practical application of Al-Zn-Mg-Cu high-strength aluminum alloy. It has high strength, low density, good fracture toughness, good fatigue performance, good stress corrosion resistance It has the characteristics of good performance and good welding performance, and has been widely used in the aerospace field. [0003] The thin-walled structure of 7055 aluminum alloy is prone to great deformation during the machining process. Severe deformation will lead to low machining accuracy and even cracking and scrapping. Heat treatment process Aging treatment can effectively reduce the residual stress in the machining process of 7055 alumi...

Claims

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Application Information

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IPC IPC(8): C22F1/053
CPCC22F1/053
Inventor 唐义号杨秀丽徐茂
Owner CHINA HELICOPTER RES & DEV INST
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