单晶叶片高温振动疲劳试验技术研究  

HCF test technology research on single crystal blade

作　　者：杜鹏飞 姜睿 李勋 刘跃聪 DU Peng-fei;JIANG Rui;LI Xun;LIU Yue-cong(AECC Shenyang Engine Research Institute,Shenyang 110043,China)

机构地区：[1]中国航空发动机集团沈阳发动机研究所,沈阳110043

出　　处：《燃气涡轮试验与研究》2022年第3期32-37,共6页Gas Turbine Experiment and Research

摘　　要：介绍了低压涡轮叶片高温振动疲劳试验方法。研究了高频感应加温原理,考虑集肤效应、端部效应,设计了高频感应加温系统,获得了均匀的温度场;通过夹具定位系统的设计,保证了更换叶片时温度场的精确性和有效性;利用理论研究结合有限元仿真,获得了高温状态下叶尖振幅与最大振动应力的关系,实现了高温环境下通过叶尖振幅对振动应力的控制。在此基础上完成了低压涡轮叶片的高温振动疲劳试验,获得了最低疲劳极限,为工程设计提供了试验依据。The method of HCF(high cycle fatigue) test with high temperature of LPT(low pressure turbine) blade was introduced. In order to simulate the equal temperature field on blade, the highfrequency induction coil was created by considering the skin effect and the end effect. Meanwhile, the clamp with position fixation was designed for the stability and validity of temperature field during blades changing. Moreover, the relationship between blade tip vibration distance and maximum stress on the blade was obtained on the base of theory research combined with finite element method, by which the stress of blade can be well controlled under high temperature condition. Finally, the HCF test was carried out and the minimum high cycle fatigue limit was obtained which can provide test basis for LPT blade engineering design.

关 键 词：航空发动机 低压涡轮叶片 振动疲劳试验 疲劳极限 高频感应 温度场 有限元 

分 类 号：V232.4[航空宇航科学与技术—航空宇航推进理论与工程]