应力比对航空高强LD2CZ铝合金腐蚀疲劳裂纹扩展的影响
Effects of Stress Ratios on Aero High-strength LD2CZ Aluminum AlloyFatigue Crack Growth with Corrosion Damage
摘 要
利用扫描电镜联合液压伺服试验机,并借助于Walker公式研究了应力比对预腐蚀不同时间航空高强LD2CZ铝合金疲劳裂纹扩展的影响,在应力比分别为0.05,0.5,0.7的条件下对预腐蚀0,15,30d的LD2CZ铝合金单边缺口板状试样进行了疲劳加载试验,得到了其疲劳裂纹扩展速率曲线,并拟合出了 Walker公式中的材料常数。结果表明:裂纹扩展速率会随着应力比的增加以及腐蚀损伤的加深而增大,拟合得到的 Walker公式可用来定量化地表征应力比和腐蚀损伤对疲劳裂纹扩展速率的影响。
应力比
腐蚀损伤
疲劳裂纹扩展
Walker公式
LD2CZ aluminum alloy
stress ratio
corrosion damage
fatigue crack growth
Walker equation
Abstract
The effects of stress ratios on fatigue cracks growth of aero high-strength LD2CZ aluminum alloywith corrosion damage were studied with Walker equation with the aid of SS550scanning electron microscopycombined with server hydraulic fatigue test machine.Fatigue tests were executed at stress ratios of 0.05,0.5,0.7for specimens with corrosion damage equivalent to 0,15,30days exposure in certain natural airport environmentrespectively.The fatigue crack growth curves were obtained,and based on that the parameters in Walker equationwere computed out.The results indicate that fatigue cracks growth rate would increase with the increase of stressratio and corrosion damage.According to the obtained Walker equation,the effects of stress ratios and corrosiondamage on the fatigue cracks growth rate could be characterized quantitatively.
中图分类号 TG145
所属栏目 试验与研究
基金项目 国家自然科学基金资助项目(11272173)
收稿日期 2013/3/26
修改稿日期
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备注李旭东(1984-),男,讲师,硕士。
引用该论文: LI Xu-dong,MU Zhi-tao,LIU Zhi-guo. Effects of Stress Ratios on Aero High-strength LD2CZ Aluminum AlloyFatigue Crack Growth with Corrosion Damage[J]. Physical Testing and Chemical Analysis part A:Physical Testing, 2013, 49(12): 781～784
李旭东,穆志韬,刘治国. 应力比对航空高强LD2CZ铝合金腐蚀疲劳裂纹扩展的影响[J]. 理化检验－物理分册, 2013, 49(12): 781～784
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参考文献
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