榫连接结构高温低周微动疲劳试验  

Low cycle fretting fatigue tests of dovetail structure at elevated temperature

作　　者：王楠 崔海涛[1] 张宏建[1] WANG Nan;CUI Haitao;ZHANG Hongjian(College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China)

机构地区：[1]南京航空航天大学能源与动力学院,南京210016

出　　处：《航空动力学报》2018年第12期3007-3012,共6页Journal of Aerospace Power

基　　金：中央高校基本科研业务费专项资金(NS2016026)

摘　　要：针对航空涡扇发动机压气机叶片/轮盘连接结构,设计了一种燕尾榫结构高温微动疲劳试验加载装置,开展了TC11钛合金在200℃及500℃下的微动疲劳试验。通过动态位移及动态应变法实现对燕尾榫微动疲劳萌生寿命的监测。试验中发现微动疲劳裂纹均萌生在燕尾榫接触区域的下边缘,且接触表面存在大量的微动磨屑,属于典型的微动疲劳失效形式。试验结果表明:温度环境对微动疲劳寿命的影响较为明显。随着试验温度的升高,试验件的微动疲劳寿命会逐渐减小。A kind of elevated temperature fretting fatigue test device of dovetail structure was designed for the compressor fan/disk connection structure of aviation turbofan engine.The fretting fatigue tests of TC11 titanium alloy at 200℃and 500℃ were carried out.The monitoring of the initiation life of dovetail fretting fatigue was achieved by dynamic displacement method and dynamic strain method.It was found that the fretting fatigue cracks were at the lower edge of the contact area of the dovetail and a large amount of abrasive scrap appeared on the contact surface as a typical fretting fatigue failure.The test results show that the effect of temperature environment on fretting fatigue life is obvious.With the increase of the test temperature,fretting fatigue life of the test specimen will gradually decrease.

关 键 词：燕尾榫 微动疲劳 试验装置 钛合金 萌生寿命 温度环境 

分 类 号：V233[航空宇航科学与技术—航空宇航推进理论与工程]