摘要
针对定向涡轮叶片的使用工况,提出了用于涡轮叶片蠕变/疲劳试验的方法,包括摩擦原理的夹具设计和标定及相关试验、计算和分析技术,并以某型定向涡轮叶片为例,介绍了该方法的实现。试验结果表明:试验方法能够模拟涡轮叶片考核截面在实际工作状态下的应力场和温度,利用所提出的试验方法和分析技术得到叶片的寿命数据是合理的。此次提出的基于构件的定向结晶涡轮叶片的蠕变/疲劳试验方法,对于涡轮叶片的定寿、故障预防、以及维修都有重要意义。
A new experimental method, in which the turbine blade was loaded by applying directionally solidified alloy turbine blade. Design of the test devices,determination of blade＇s key section and the equivalent accelerated test loading-spectrum, test data analysis etc. was described in detail. Test results show that the method can simulate turbine blade key section＇s working “stress field”and temperature in the laboratory and give reasonable life data for turbine blade. The safe service life of aeroengine component determined by the component creep/fatigue tests will be more accurate than that obtained with the plain specimen.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2005年第6期925-931,共7页
Journal of Aerospace Power
基金
航空科学基金资助(02C51031)
全国优秀博士学位论文作者专项资金资助(200351)
关键词
航空
航天推进系统
涡轮叶片
定向结晶
蠕变/疲劳
试验技术
aerospace propulsion system
turbine blade
directionally solidified alloy
creep/fatigue
experimental technology
