穿透型疲劳裂纹扩展与铝合金局部点蚀损伤特征参数的依存性分析
Dependent Analysis of Through Out Crack Propagation on Localized Pitting Corrosion Parameters of Aluminum Alloy
摘 要
铝合金的腐蚀以点蚀特征为代表, 在腐蚀介质的侵袭下, 其构件表面会出现大量的腐蚀坑。这些腐蚀损伤特征对于局部的应力应变产生影响, 并且伴随着氢的渗入材料局部的脆性增强, 对于临近裂纹的扩展会产生较大的影响。通过建立与局部点蚀损伤特征参数相关的裂纹扩展表征模型表征局部腐蚀对于临近的裂纹扩展影响程度, 对于铝合金结构的腐蚀损伤容限评估具有参考价值。
裂纹扩展
局部腐蚀损伤
表征参数
临界距离理论
fatigue
crack propagation
localized corrosion damage
characteristic parameter
theory of critical distance
Abstract
Pitting corrosion morphology prevails on aluminum alloy surface subjected to corrosive media in service environment, which will change the distribution of local stress and strain and local area may become brittle as the penetration of hydrogen may accompany corrosion process. Such local change will significantly influence the fatigue crack propagation in vicinity. The present thesis tries to establish a model to characterize the influence of local corrosion on fatigue crack propagation nearby based on local corrosion damage characteristic parameters, which is of reference value for corrosion damage tolerance evaluation.
中图分类号 TG174.3 V252 DOI 10.11973/fsyfh-201511008
所属栏目 试验研究
基金项目 国家自然科学基金(1072124)
收稿日期 2014/10/30
修改稿日期
网络出版日期
作者单位点击查看
备注李旭东(1984-),讲师,硕士,从事金属结构的腐蚀疲劳问题的研究,
引用该论文: LI Xu-dong,KONG Guang-ming,MU Zhi-tao. Dependent Analysis of Through Out Crack Propagation on Localized Pitting Corrosion Parameters of Aluminum Alloy[J]. Corrosion & Protection, 2015, 36(11): 1049
共有人对该论文发表了看法，其中：
人认为该论文很差
人认为该论文较差
人认为该论文一般
人认为该论文较好
人认为该论文很好
参考文献
【1】ASTM STP 486Damage tolerance in aircraft structures[S].
【2】李旭东, 穆志韬, 刘治国,等. 预腐蚀铝合金材料裂纹萌生寿命评估[J]. 装备环境工程, 2012, 9(5):24-28.
【3】WEI R P,HARLOW D G. Corrosion and corrosion fatigue of aluminium alloys-an aging aircraft issue[C]//Proceedings of the Seventh International Fatigue Congress. Houston Texas:[s.n.],1999:2197-2204.
【4】LI X D,WANG X S,REN H H,et al. Effect of prior corrosion state on the fatigue small cracking behavior of 6151-T6 aluminum alloy[J]. Corrosion Science,2012,55:26-33.
【5】李旭东, 穆志韬, 刘治国. 应力比对航空高强度铝合金腐蚀疲劳裂纹扩展的影响[J]. 理化检验-物理分册,2012,49(12):781-784.
【6】李旭东,刘治国,穆志韬,等. 基于飞行载荷的LC9铝合金腐蚀疲劳裂纹扩展研究[J]. 腐蚀与防护,2013,34(11):985-988.
【7】NEWMAN J C,RAJU I S. An empirical stress-intensity factor equation for the surface crack[J]. Engineering Fracture Mechanics,1981,15(5):185-192.
【8】PETERSON R E. Notch-sensitivity[C]//Metal fatigue. New York:McGraw Hill,1959:293-306.
【9】TAYLOR D. Analysis of fatigue failures in components using the theory of critical distances[J]. Eng Fail Anal,2005,12(6):6-14.
【10】DAVID T. The theory of critical distances-A new perspective in fracture mechanics[M]. London:ELSEVIER,2007.
【2】李旭东, 穆志韬, 刘治国,等. 预腐蚀铝合金材料裂纹萌生寿命评估[J]. 装备环境工程, 2012, 9(5):24-28.
【3】WEI R P,HARLOW D G. Corrosion and corrosion fatigue of aluminium alloys-an aging aircraft issue[C]//Proceedings of the Seventh International Fatigue Congress. Houston Texas:[s.n.],1999:2197-2204.
【4】LI X D,WANG X S,REN H H,et al. Effect of prior corrosion state on the fatigue small cracking behavior of 6151-T6 aluminum alloy[J]. Corrosion Science,2012,55:26-33.
【5】李旭东, 穆志韬, 刘治国. 应力比对航空高强度铝合金腐蚀疲劳裂纹扩展的影响[J]. 理化检验-物理分册,2012,49(12):781-784.
【6】李旭东,刘治国,穆志韬,等. 基于飞行载荷的LC9铝合金腐蚀疲劳裂纹扩展研究[J]. 腐蚀与防护,2013,34(11):985-988.
【7】NEWMAN J C,RAJU I S. An empirical stress-intensity factor equation for the surface crack[J]. Engineering Fracture Mechanics,1981,15(5):185-192.
【8】PETERSON R E. Notch-sensitivity[C]//Metal fatigue. New York:McGraw Hill,1959:293-306.
【9】TAYLOR D. Analysis of fatigue failures in components using the theory of critical distances[J]. Eng Fail Anal,2005,12(6):6-14.
【10】DAVID T. The theory of critical distances-A new perspective in fracture mechanics[M]. London:ELSEVIER,2007.
相关信息
