Abstract:The fatigue damage resistance to different corrosion environments in 7475-T7351 aluminum alloy was investigated.It was carried out by axial load fatigue test,fatigue crack growth rate test under different environments.The results show that corrosive environment affects the fatigue resistance of 7475-T7351 aluminum alloy dramatically,and the fatigue strength of smooth specimen in fuel tank or in 3.5%(mass fraction)NaCl solution decreases by 68% in comparision to room temperature,and the influence of different environments including water in fuel tank and 3.5%NaCl solution on the fatigue strength of materials is almost the same.The different corrosion environments and different temperature on low cycle fatigue in 7475-T7351 are less effective.The corrosive environment accelerates strongly the rate of fatigue crack propagation.The water in fuel tank and 3.5% NaCl solution all accelerate fatigue crack propagation by almost the same pattern.
宫玉辉, 刘铭, 张坤, 黄敏, 伊琳娜, 戴圣龙. 不同腐蚀环境对7475-T7351铝合金疲劳性能及裂纹扩展速率的影响[J]. 材料工程, 2010, 0(9): 71-73.
GONG Yu-hui, LIU Ming, ZHANG Kun, HUANG Min, YI Lin-na, DAI Sheng-long. Effects of Different Corrosion Environments on Fatigue Property and Crack Growth Rate in 7475-T7351 Aluminum Alloy. Journal of Materials Engineering, 2010, 0(9): 71-73.
[1]ROBERT P WEI.Corrosion and Corrosion Fatigue of Airframe Materials[M].Washington,D.C.:Available through the National Technical Information Service,2000. [2]蒋祖国.飞机结构腐蚀疲劳[M].北京:航空工业出版社,1992.39-40. [3]鲍蕊,张建宇,费斌军.潮湿空气环境对2024-T3铝合金疲劳性能的影响[J].材料研究学报,2007,21(5):548-550. [4]SHIPILOV S A.腐蚀疲劳裂纹扩展的机理[J].中国腐蚀与防护学报,2004,24(6):321-333. [5]ZAMBER J E,HILLBERRY B M.A probabilistic approach to predicting fatigue lives of corroded 2024-T3[J].AIAA,1999,37(10):1311-1317. [6]杨胜,易丹青,杨守杰,等.腐蚀环境下2E12航空铝合金疲劳裂纹扩展行为研究[J].材料工程,2007,(12):26-29. [7]秦剑波,王生楠,刘亚龙,等.腐蚀环境下2024-T3铝合金疲劳裂纹扩展和剩余强度试验研究[J].材料工程,2006,(3):14-17. [8]杨晓华,姚卫星,段成美.腐蚀环境下LC4铝合金疲劳损伤累积规律研究[J].航空材料学报,2003,24(3):234-236. [9]ASTM STP1298,pitting corrosion and fatigue crack nucleation,effects of the environment on the initiation of crack growth[S]. [10]LAROUCHE S,BERNAD M,BUI_QUOC T,et al.Influence of cold working and interference fit on fatigue life of 7475-T7351 aluminum alloy fastener hole[A].Design for Durability in the Digital Age vol II-21st Symposium of the International Committee on Aeronautical Fatigue(ICAF 2001)[C].Toulouse,France:ICAF,2001.681-698. [11]刘铭,张坤,黄敏,等.7475-T7351铝合金抗疲劳性能研究[J].稀有金属,2009,33(5):626-630. [12]KASSIM S,AL-RUBAIEEMERSON K L,BARROSOLEONARDO B.Fatigue crack growth analysis of pre-strained 7475-T7351 aluminum alloy[J].International Journal of Fatigue,2006,(28):934-942. [13]KIM SANG TAE,TADJIEV DAMIR,YANG HYUN TAE.Fatigue life prediction under random loading conditions in 7475-T7351 aluminum alloy using the RMS model[J].International Journal of Damage Mechanics,2006,15(1):89-102.