摘要
针对航空发动机压气机转子叶片的结构和工作特点,通过有限元方法对叶片进行模态分析,研究叶片的"频率转向"和"振型转换"现象,揭示了动频曲线转向趋势和振型耦合规律,并讨论了温度场对叶片“频率转向”特性的影响,分析叶片动频特性的详细变化规律,为叶片振动特性设计与考核提供了理论基础。
According to the structure and operation status of the aero-engine compressor blade, modal analysis based on the Finite Element Method was established in order to investigate the frequency veering and modal shape interaction phenomenon.The veering trending of the dynamic frequency curve and modal shape coupling law were revealed.The interaction of temperature field on frequency veering characteristics of the blade was discussed as while.The research results may provide foundation for the compressor blade vibration design assessment.
作者
牛宏伟
郭海东
文敏
NIU Hong-wei;GUO Hai-dong;WEN Min(China Flight Test Establishment, Xi′an Shaanxi 710089, China)
出处
《机械研究与应用》
2019年第3期37-39,共3页
Mechanical Research & Application
关键词
压气机转子叶片
频率转向
转速
温度场
模态耦合
compressor blade
frequency veering
rotating speed
temperature field
mode coupling
