压气机叶片振动超限测试分析  

Measurement technology of vibration overrun of compressor blade

作　　者：樊嘉峰 余华蔚 张军 巩岁平 赵燕立 FAN Jia-feng;YU Hua-wei;ZHANG Jun;GONG Sui-ping;ZHAO Yan-li(AECC Sichuan Gas Turbine Establishment,Mianyang 621000,China)

机构地区：[1]中国航发四川燃气涡轮研究院,四川绵阳621000

出　　处：《燃气涡轮试验与研究》2022年第4期26-29,共4页Gas Turbine Experiment and Research

摘　　要：某型航空发动机高压压气机试验件,在静叶角度调节状态、换算转速0.9时进行的性能参数录取试验中,在距喘振边界还有一段距离的状态下,发生了一级转子叶片振动超限。利用试验前在该试验件多级转子叶尖和转子出口安装的动态压力测点测得的叶尖泄漏流和出口尾迹流等复杂涡系的非定常流动数据,分析了导致一级叶片振动超限的不稳定因素的来源。The performance parameters of the high pressure compressor of an aero-engine were obtained at the corrected speed of 0.9, and the blade vibration of the first stage rotor exceeded the limit when there was a distance from the surge boundary. In this compressor, a detailed measurement scheme was developed in advance. The unsteady flow measurement of complex vortex systems was realized, such as tip leakage and exit wake flow. In view of the instability phenomenon of the compressor test, the source of the instability factors were analyzed through the dynamic pressure test data of multi-directional monitoring.

关 键 词：航空发动机 压气机 叶片振动 动压叶型探针 尾迹流测试 高频采集 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]