摘要
针对某小型涡喷发动机转子的实际结构,在ANSYS中建立了三维有限元模型。计算了前2阶固有模态和振型,并与试验模态分析结果进行了对比,结果表明,该计算模型得到的数据与试验模态结果基本一致。在此基础上,对转子的临界转速进行了计算。
The three-dimensional finite element model was established based on ANSYS for a turbojet engine rotor structure. The first-and second-order natural frequencies and mode shapes were calculated, and the results contrasted with the experimental results. The results show that the calculation data is in accord with the experimental mode results. The rotor critical speed was calculated based on the results.
出处
《航空发动机》
2009年第5期30-31,51,共3页
Aeroengine
关键词
临界转速
航空发动机
有限元法
动力特性
critical speed
aeroengine
finite element method
dynamic characteristics
作者简介
王海朋（1980），男。硕士，从事无人机动力、小型涡喷航空发动机的设计与研究工作。
