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Method for conducting boric sulfuric acid anodization pretreatment on 7A85-T7452 aluminum alloy aeronautical part

A technology of 7A85-T7452 and aviation parts, which is applied in the field of boron-sulfuric acid anodization pretreatment of 7A85-T7452 aluminum alloy aviation parts, can solve the problems of easy generation of network grain boundaries, adverse effects of fatigue life, and original grain boundary corrosion traces, etc. Achieve the effects of improving corrosion resistance and fatigue performance, eliminating oxide film defects, and improving compactness and continuity

Inactive Publication Date: 2017-05-10
AVIC BEIJING INST OF AERONAUTICAL MATERIALS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The general anodizing pretreatment process is alkali washing or mixed acid (nitric acid, hydrofluoric acid, chromic anhydride, etc.) deoxidation. This method makes the surface of the part prone to reticular grain boundaries, and the original grain boundary corrosion marks appear, which has a great impact on the fatigue life. increase adverse effects

Method used

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  • Method for conducting boric sulfuric acid anodization pretreatment on 7A85-T7452 aluminum alloy aeronautical part
  • Method for conducting boric sulfuric acid anodization pretreatment on 7A85-T7452 aluminum alloy aeronautical part

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Effect test

Embodiment 1

[0032] Table 1 shows the fatigue life effect of the parts prepared by the present invention through machining-hole mechanical extrusion treatment-surface shot peening treatment-boric acid anodization and other processes. in:

[0033] (1) Hole treatment, select an alloy steel rod 0.40mm larger than the initial hole, apply force to make it pass through the hole on the part, so as to complete the extrusion of the hole wall. Then the extruded holes are reamed and made to meet the requirements of the design drawings.

[0034] (3) Surface shot peening treatment

[0035] 0.70mm cast steel shot is selected as the shot peening medium, and the surface of the part is shot peened with a shot peening intensity of 0.15A and a shot peening coverage rate of 100% to 200%.

[0036] (4) surface anodized treatment

[0037] The surface anodization of parts adopts boric acid anodization process, the process parameters are: sulfuric acid concentration 40g / L sulfuric acid, boric acid concentration...

Embodiment 2

[0041] Table 2 shows the fatigue life effect of parts prepared by the process of machining-hole shot peening-surface shot peening-bororic acid anodization and other processes according to the present invention. in:

[0042] (1) hole treatment

[0043] 0.70mm cast steel shot is selected as the shot peening medium, and the hole wall is shot peened. The shot peening intensity is 0.15A, and the shot peening coverage rate is 100% to 200%.

[0044] (3) Surface shot peening treatment

[0045] 0.70mm cast steel shot is selected as the shot peening medium, and the surface of the part is shot peened with a shot peening intensity of 0.15A and a shot peening coverage rate of 100% to 200%.

[0046] (4) surface anodized treatment

[0047] The surface anodization of parts adopts boric acid anodization process, the process parameters are: sulfuric acid concentration 40g / L sulfuric acid, boric acid concentration 8g / L, bath temperature 20~25℃, oxidation time 22 minutes, oxidation voltage 13~...

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Abstract

The invention belongs to the technical field of aluminum alloy aeronautical part manufacturing and relates to a method for conducting boric sulfuric acid anodization pretreatment on a 7A85-T7452 aluminum alloy aeronautical part. The method comprises the steps of machining of the part, hole treatment, surface treatment, degreasing treatment and surface anodization treatment. The method is targeted at the characteristic that a 7A85-T7452 aluminum alloy has the strong interior sub-grain texture, and the hole treatment process and the surface treatment process for the part are added to the boric sulfuric acid anodization pretreatment phase. By means of hole diameter squeezing or shot blasting treatment conducted on holes and surface shot blasting treatment conducted on the part, surface integrity of the part is effectively restored, and thus compactness and continuity of a boric sulfuric acid anodization oxidation film layer of the part are improved; defects of the oxidation film layer are decreased or eliminated; and damage resistance of the part is improved. By means of the method, corrosion resistance of the part can be improved, and the fatigue life of the part can be prolonged; and in addition, an operation process is easy and convenient to conduct, additional production facilities do not need to be built, and production control can be conducted conveniently.

Description

technical field [0001] The invention belongs to the technical field of manufacturing aluminum alloy aviation parts, and relates to a pretreatment method for boron-sulfuric acid anodization of 7A85-T7452 aluminum alloy aviation parts. Background technique [0002] With the further development of technology, higher requirements are put forward for the service life and environmental tolerance of the main load-bearing structure of the new generation of aircraft. New materials and new technologies have been widely used. 7A85-T7452 aluminum alloy forging is a manufacturing A new generation of material for large and complex main load-bearing components of aircraft, and its parts have better fatigue life. The main components of 7A85-T7452 aluminum alloy contain about 1.6% Cu, 1.5% Mg, 7.50% Zn and 0.12% Zr. The 7A85-T7452 aluminum alloy forging has a high subgrain texture strengthening and toughening effect. During the preparation process, two-stage artificial forced aging treatmen...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C25D11/16C25D11/08
CPCC25D11/16C25D11/08
Inventor 冯朝辉陈高红何维维王亮李惠曲
Owner AVIC BEIJING INST OF AERONAUTICAL MATERIALS
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