摘要
建立了一个轴向可自由伸缩的双转子系统计算模型,采用有限元法,分析了温度场对该双转子系统动力特性的影响。参照航空发动机转子系统的温度分布情况,通过ANSYS软件构造了该双转子系统的稳态温度场。分别在常温状态、考虑整体温度场、只考虑轴的温度场以及只考虑盘的温度场4种情况下,计算了该双转子系统的临界转速和不平衡响应,并进行了对比分析。结果表明,温度场作用下双转子系统的临界转速要比常温状态下的低,内、外转子分别为主激励的第一阶临界转速相对误差都已接近6%。盘的温度对于转子系统动力特性的影响要比轴的温度小得多。
A dual-rotor calculation model which can expand freely in the axial direction is established in this paper, and the effects of temperature field on dynamic characteristics of this dual-rotor system are analyzed with finite element method. With reference to the temperature distribution of an aero-engine rotor system, a steady-state temperature field of the dual-rotor system is constructed with ANSYS software. The critical speeds and unbalanced responses of the system under four different conditions, namely, ignoring the temper- ature field, considering the whole rotor system temperature field, only considering the temperature field of the shaft, and only considering the temperature fields of the disk are calculated respectively, and the results are compared and analyzed. It shows that the critical speeds of the dual-rotor system under the temperature field are lower than those under normal temperature. The relative errors of first critical speeds excited by the inner rotor and outer rotor respectively are both close to 6%. The effects of the disk temperature on the dy- namic characteristics of dual-rotor system are much smaller than those of the shaft temperature.
出处
《沈阳航空航天大学学报》
2013年第1期34-38,共5页
Journal of Shenyang Aerospace University
关键词
温度场
双转子系统
临界转速
不平衡响应
temperature field
dual-rotor system
critical speeds
unbalance response
