某燃气轮机压气机叶片振动特性研究

Vibration Analysis of the Compressor Blade in a Gas Turbine

针对某燃气轮机压气机叶片断裂故障,通过理论计算和试验方法,对故障级叶片在与轮盘耦合条件下的振动特性进行了研究分析。理论计算叶片动频时考虑了旋转离心力和温度载荷的影响,利用有限元计算程序ANSYS WORKBENCH循环对称分析功能和接触分析功能,完成了压气机叶片振动分析,通过坎贝尔图得到叶片1阶弯曲共振转速为6 900 r/min。随后,在整机状态下,利用非接触式微波测量方法,对该级动叶进行了振动测试,获得的叶片1阶弯曲共振转速为6 988 r/min,实测得到的共振转速与理论计算结果吻合,为故障的进一步排查提供有利的理论和试验依据。

For the failure of the compressor blade in a gas turbine,the vibration analysis of the compressor blade under disc coupled structure is performed through theoretical calculation and experimental. Through the use of the cyclic symmetry function and the contact function of the ANSYS WORKBENCH,a computational analysis on vibration of the blade disc in low compressor has been conducted.During the calculation,the effect has been taken into account of the rotating centrifugal force and temperature-dependent material parameters on the dynamic frequency characteristic of the blade.The resonance rotational speed obtained by Campbell diagram is 6 900 r/min.Then,vibration testing on the failed rotor blade under the whole gas turbine running has been completed by using non-contact microwave method.The resonance rotational speed obtained through the method is 6 988 r/min.The results show that the obtained harmonic resonance rotational speed is found to be in agreement with the theoretical calculation resuhs, providing useful foundation for further failure analysis.