Depth Extension Evaluation of Fatigue Cracks Initiated from Corrosion Pits on Aluminum Alloy 7A09 with Prior Corrosion Damage
摘 要
含初始缺陷铝合金结构的寿命评估方法大多需要用到裂纹扩展深度这一难以直接测得的参数,为了找到其与表面裂纹长度之间的关系,对预腐蚀7A09铝合金进行疲劳试验,并利用扫描电镜结合能谱仪进行疲劳断口分析,发现了腐蚀坑处萌生裂纹沿着深度方向的扩展规律。结果表明:7A09铝合金的疲劳断口多呈脆性断裂特征,富集的增强相反而会成为脆性相,降低材料的塑性变形能力;对于单一裂纹源主导的疲劳断裂,其内部扩展深度与表面裂纹长度之间存在线性关系,通过检测构件中裂纹的表面长度可以获得其扩展深度,对于结构剩余寿命的估算具有参考价值;对于多源疲劳,裂纹扩展长度与深度间无确定的关系。。
Abstract
The present fatigue life evaluation approach for aluminum alloy containing defects is based on depth extension of crack which is hidden inside and hard to be directly obtained. In order to find the relation between depth extension and surface cracks length, fatigue experiment was carried out on aluminum alloy 7A09 with prior corrosion damage, and propagation rules of corrosion pit cracks along depth direction was found by analyzing the fatigue fracture by using scanning electron microscope and energy disperse microscope. Results indicate that the fatigue fratography exhibits brittle fracture morphology, and the accumulation of the second phase particles will inversely enhance embrittlement by reducing plasticity. For fracture dominated by solo crack, the depth extension and the surface length of crack displays a linear relationship which provide a way to evaluate depth extension of a crack based on the detectable surface length, which is valuable to residual life prediction of structure. For multiple fatigue, there is uncertain relation between extension length and depth of crack.
中图分类号 TG132 DOI 10.11973/jxgccl201701005
所属栏目 试验研究
基金项目 国家自然科学基金资助项目(1072124)
收稿日期 2015/11/30
修改稿日期 2016/12/8
网络出版日期
作者单位点击查看
备注李旭东(1984-),男,辽宁丹东人,讲师,硕士。
引用该论文: LI Xu-dong,LIU Yuan-hai,LIU Zhi-guo,ZHU Ze-long. Depth Extension Evaluation of Fatigue Cracks Initiated from Corrosion Pits on Aluminum Alloy 7A09 with Prior Corrosion Damage[J]. Materials for mechancial engineering, 2017, 41(1): 25~29
李旭东,刘元海,刘治国,朱泽龙. 预腐蚀7A09铝合金腐蚀坑处萌生疲劳裂纹扩展深度的估算[J]. 机械工程材料, 2017, 41(1): 25~29
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参考文献
【1】范红妹, 曾燕屏, 王习术,等. 夹杂物特征参数对拉伸载荷下超高强度钢疲劳裂纹萌生与扩展的影响[J]. 航空材料学报, 2007, 27(4):6-9.
【2】王苗苗, 曾燕屏, 王习术,等. 航空用超高强度钢疲劳裂纹表面长度与内部长度之间的关系[J]. 航空材料学报, 2009, 29(3):102-106.
【3】李旭东. 铝合金腐蚀环境下疲劳短裂纹演化规律的表征[D]. 北京:清华大学,2011.
【4】李旭东,刘治国,穆志韬. 基于短裂纹的LD10CZ铝合金腐蚀预疲劳裂纹扩展[J]. 海军航空工程学院学报,2013,21(1):47-52.
【5】LI X D, WANG X S, REN H H, et al. Effect of prior corrosion state on the fatigue small cracking behaviour of 6151-T6 aluminum alloy[J]. Corros Sci, 2012, 55(2):26-33.
【6】冯西桥,何树延.表面裂纹疲劳扩展的一种损伤力学方法[J]. 清华大学学报(自然科学版), 1997, 37(5):78-82.
【7】WEI R P, LANDES J D. Correlation between sustained-load and fatigue crack growth in high strength steels[J]. Materials Research and Standard, 1977, 9(7):25-28.
【8】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.
【9】ELBER W. Damage tolerance in aircraft structures[C]//ASTM STP 486, American Society for Testing and Materials.[S.l.]:[s.n.], 1971:230-242.
【10】WANG X. On the quantification of the constraint effect along a three-dimensional crack front[C]//Proceeding of the 7th International ASEM/ESIS Symposium on Fatigue and Fracture Mechanism. Atlanta:[s.n.], 2007:87-102.
【11】通旭东, 李全通, 史永芳, 等. 表面带不同轻微损伤钛合金的超高周疲劳性能[J]. 机械工程材料, 2013, 37(9):9-12.
【12】张海威, 何宇廷, 范超华, 等. 2A12铝合金不同方法腐蚀疲劳的寿命及断口形貌[J]. 机械工程材料, 2012, 36(5):26-28, 32.
【2】王苗苗, 曾燕屏, 王习术,等. 航空用超高强度钢疲劳裂纹表面长度与内部长度之间的关系[J]. 航空材料学报, 2009, 29(3):102-106.
【3】李旭东. 铝合金腐蚀环境下疲劳短裂纹演化规律的表征[D]. 北京:清华大学,2011.
【4】李旭东,刘治国,穆志韬. 基于短裂纹的LD10CZ铝合金腐蚀预疲劳裂纹扩展[J]. 海军航空工程学院学报,2013,21(1):47-52.
【5】LI X D, WANG X S, REN H H, et al. Effect of prior corrosion state on the fatigue small cracking behaviour of 6151-T6 aluminum alloy[J]. Corros Sci, 2012, 55(2):26-33.
【6】冯西桥,何树延.表面裂纹疲劳扩展的一种损伤力学方法[J]. 清华大学学报(自然科学版), 1997, 37(5):78-82.
【7】WEI R P, LANDES J D. Correlation between sustained-load and fatigue crack growth in high strength steels[J]. Materials Research and Standard, 1977, 9(7):25-28.
【8】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.
【9】ELBER W. Damage tolerance in aircraft structures[C]//ASTM STP 486, American Society for Testing and Materials.[S.l.]:[s.n.], 1971:230-242.
【10】WANG X. On the quantification of the constraint effect along a three-dimensional crack front[C]//Proceeding of the 7th International ASEM/ESIS Symposium on Fatigue and Fracture Mechanism. Atlanta:[s.n.], 2007:87-102.
【11】通旭东, 李全通, 史永芳, 等. 表面带不同轻微损伤钛合金的超高周疲劳性能[J]. 机械工程材料, 2013, 37(9):9-12.
【12】张海威, 何宇廷, 范超华, 等. 2A12铝合金不同方法腐蚀疲劳的寿命及断口形貌[J]. 机械工程材料, 2012, 36(5):26-28, 32.
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