摘要
通过建立的高温涡轮叶片振动疲劳试验系统,实现了高温条件下对发动机涡轮叶片及材料振动疲劳试验的闭环控制,有效提升了试验的控制精度和测量精度。采用在试样表面粘贴高温应变计的方式,对试验件的高温振动应变进行直接测量,实现了高温条件下的振动应力标定。与传统替换法试验结果进行对比分析,结果表明二者所得结果具有明显差异。针对航空发动机单晶涡轮叶片开展了高温振动疲劳试验测试,通过升降法得到了该型叶片在800℃、2×107循环条件下对应的中值疲劳极限。试验结果满足发动机设计所需的置信度要求。
A high temperature vibration fatigue testing system for turbine blades, with a close loop control method, was established to effectively improve the measurement and control accuracy. During the vibration fatigue test, the high-temperature strain was obtained by high temperature strain gauges directly at the turbine surface to realize vibration stress calibration at high temperature. The test results are compared with the traditional indirect calibrate method. The results show that the two methods have a significant difference. A group of single-crystal turbine blades was tested at 800 ℃, and the median vibration fatigue limit corresponding to 2×10~7 cycles was finally obtained by the stair-case test. The testing results meet the data confidence requirement for engine design.
作者
杨宪峰
陈新
许巍
何玉怀
YANG Xian-feng;CHEN Xin;XU Wei;HE Yu-huai(Beijing Key Laboratory of Aeronautical Materials Testing and Evaluation,AECC Key Laboratory of Science and Technology on Aeronautical Materials Testing and Evaluation,AECC Beijing Institute of Aeronautical Materials,Beijing 100095,China)
出处
《燃气涡轮试验与研究》
2022年第4期30-34,共5页
Gas Turbine Experiment and Research
基金
军工院所财政稳定支持项目(KZ0C190728)
国家自然科学基金(91860112)。
关键词
航空发动机
振动疲劳试验
高温振动
涡轮叶片
高温应变计
闭环控制
aero-engine
vibration fatigue test
high-temperature vibration
turbine blade
high-temperature strain gauge
close-loop control
