摘要
针对航空发动机压气机叶片腐蚀环境下的超高周疲劳问题,研究了盐雾腐蚀对Ti-6Al-4V钛合金超高周疲劳性能的影响。首先对试件进行加速腐蚀处理,然后对未腐蚀和腐蚀后的两种钛合金试件进行了超高周疲劳试验。试验结果表明:Ti-6Al-4V钛合金试件具有较强的耐腐蚀性,腐蚀后试件的超高周疲劳寿命没有明显降低。S-N曲线显示,腐蚀前后试件的S-N曲线两条曲线均呈连续下降趋势,并不存在传统疲劳概念上的无限寿命。断口分析表明:疲劳寿命低于108次时,两种类型的试件裂纹均萌生于表面;当循环寿命超过108次时,部分未经腐蚀处理的试件裂纹萌生在内部,成类似"鱼眼"状,腐蚀后试件疲劳裂纹萌生在试件腐蚀的表面处。
Aiming at the problem of Very High Circle Fatigue （VHCF） of aero engine compressor blade in corrosion environment, the effect of salt spray corrosion on the VHCF performance of Ti-6Al- 4V titanium alloy was studied. Firstly, the specimens were subjected to accelerated corrosion treatment, then, very high cycle fatigue experiment was carried out for two kinds of specimen including corroded and not corroded titanium alloy. Experimental results indicate that Ti-6Al-4V titanium alloy specimen has relatively strong corrosion resistance; the very high cycle fatigue life of specimen does not decrease significantly after corrosion treatment. S-N curve show that both curves present continuous downtrend, does not exist the infinite life which comes from traditional fatigue concept. Fracture surface analysis indicates that when fatigue life is lower than 108 times, the cracks of two kinds of specimens initiate on the surface; when fatigue life is higher than 10^8 times, the cracks initiate in the interior of a part of uncorroded specimens and are as similar as ＂fish eye＂ type, while the cracks initiate on corroded surface of corroded specimen.
作者
鲁凯举
程礼
陈煊
焦胜博
陈皎
谢祥勇
LU Kai-ju CHENG Li CHEN Xuan JIAO Sheng-bo CHEN Jiao XIE Xiang-yong(Air Force Engineering University, Xi＇ an 710038, China Co-Innovation Center for Advanced Aero-Engine, Beijing 100000, China 94855 Troops Information Support Station, Quzhou 324000, China)
出处
《实验力学》
CSCD
北大核心
2016年第6期795-802,共8页
Journal of Experimental Mechanics
基金
国家自然科学基金青年人才项目(11402302)
陕西省自然科学基金(2016JQ1031)
第59批博士后基金面上一等资助
