李旭东,张连峰,朱武峰,丁文勇.铝合金高温低周疲劳裂纹扩展可靠性评估[J].装备环境工程,2013,10(5):134-138. LI Xu-dong,ZHANG Lian-feng,ZHU Wu-feng,DING Wen-yong.Reliability Evaluation of Aluminum Alloy under High Temperature Based on Low CycleFatigue Crack Growth[J].Equipment Environmental Engineering,2013,10(5):134-138.
铝合金高温低周疲劳裂纹扩展可靠性评估
Reliability Evaluation of Aluminum Alloy under High Temperature Based on Low CycleFatigue Crack Growth
投稿时间：2013-04-26  修订日期：2013-09-01
DOI：10.7643/issn.1672-9242.2013.05.030
中文关键词:  铝合金  高温  可靠性  疲劳裂纹扩展
英文关键词:aluminum alloy  high temperature  reliability  fatigue crack growth
基金项目:
作者单位
李旭东 海军航空工程学院青岛校区，山东青岛266041 
张连峰 海军航空工程学院青岛校区，山东青岛266041 
朱武峰 海军航空工程学院青岛校区，山东青岛266041 
丁文勇 海军航空工程学院青岛校区，山东青岛266041 
AuthorInstitution
LI Xu-dong Reliability Evaluation of Aluminum Alloy under High Temperature Based on Low CycleFatigue Crack GrowthQingdao Campus of Naval Aeronautical Academy，Qingdao266041，China 
ZHANG Lian-feng Reliability Evaluation of Aluminum Alloy under High Temperature Based on Low CycleFatigue Crack GrowthQingdao Campus of Naval Aeronautical Academy，Qingdao266041，China 
ZHU Wu-feng Reliability Evaluation of Aluminum Alloy under High Temperature Based on Low CycleFatigue Crack GrowthQingdao Campus of Naval Aeronautical Academy，Qingdao266041，China 
DING Wen-yong Reliability Evaluation of Aluminum Alloy under High Temperature Based on Low CycleFatigue Crack GrowthQingdao Campus of Naval Aeronautical Academy，Qingdao266041，China 
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中文摘要:
      通过对不同温度下6151-T6合金的研究，获得了一种基于可靠性理论的裂纹扩展速率表达式，为预测6151-T6铝合金构件的安全寿命提供依据。该表达式表明，在高温条件下，6151-T6铝合金疲劳裂纹扩展存在门槛值，而且该门槛值会随着环境温度的升高而降低。
英文摘要:
      Fatigue crack growth rate of AA6151-T6in high temperature was tested. The fatigue crack growth rate formula was obtained based on reliability theory. The result showed that fatigue crack growth of AA6151-T6exists threshold value in high temperature, which decreases with temperature increasing. The purpose was to provide reference for safe life prediction of AA 6151-T6component.The present thesis made a research on the fatigue crack growth rate of AA6151-T6subjected to various elevated, and proposed a reliability based formula to evaluate FCG, which provided the basis of 6151-T6 aluminum alloy component safe life prediction. The method demonstrates the existence of fatigue crack growth threshold value of 6151-T6 aluminum alloy subjected to elevated temperature, which decreases with temperature increasing.
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