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    航空用6061铝合金恒载荷应力腐蚀行为

    Stress Corrosion Behavior of 6061 Aluminum Alloy for Aviation under Constant Load

    • 摘要: 采用恒载荷全浸腐蚀拉伸、断口扫描和室温拉伸等方法研究了拉应力对两种热处理状态6061铝合金(6061-T4和6061-T6)应力腐蚀行为的影响。结果表明,在O2和Cl-共存环境中,6061-T4铝合金的应力腐蚀敏感性很低,力学性能降低主要受腐蚀介质的电化学腐蚀影响;6061-T6铝合金的应力腐蚀开裂敏感性高于6061-T4铝合金,其应力腐蚀开裂倾向受腐蚀影响为主,力学因素影响为辅;应力腐蚀后,6061-T4和6061-T6铝合金表层腐蚀区域为沿晶脆断,次表层为准解离断裂,中心为穿晶断裂;在腐蚀介质与应力同时作用下,6061-T4铝合金由点蚀发展为晶间腐蚀,并随应力增大变为剥落腐蚀;6061-T6铝合金点蚀不明显,但晶间腐蚀深度随应力增大而加深。

       

      Abstract: The effect of tensile stress on stress corrosion properties of aluminum alloy at different heat-treatment states (6061-T4 and 6061-T6) were studied by means of constant load full immersion corrosion tensile, fracture scanning and room temperature tensile methods. The results showed that in the coexistence of O2 and Cl-, the stress corrosion sensitivity of 6061-T4 aluminum alloy was very low, and the degradation of mechincal properties was mainly affected by the electrochemical corrosion of corrosive medium. The stress corrosion cracking sensitivity of the 6061-T6 aluminum alloy was higher than that of the 6061-T4 aluminum alloy, and the stress corrosion cracking tendency of the 6061-T6 aluminum alloy were mainly affected by corrosion and supplemented by mechanical factors. The surface corrosion areas of both aluminum alloys after stress corrosion were intergranular brittle fracture, the subsurfaces were quasi-dissociative fracture, and the centers were transgranular fracture.Under the simultaneous action of corrosive medium and stress, the corrosion of 6061-T4 aluminum alloy developed from pitting corrosion to intergranular corrosion, and finally became exfoliation corrosion as the stress increased. Pitting corrosion in 6061-T6 aluminum alloy was not obvious, but the depth of intergranular corrosion increased with stress.

       

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