为了对压气机盘和涡轮盘低循环疲劳寿命分析提供温度场数据，采用ANSYS计算软件的热分析模块对某型航空发动机高压压气机转子瞬态温度场和低压涡轮转子三维稳态温度场进行计算研究。重点分析旋转盘腔、旋转轴系、封严篦齿、榫头装配间隙等部位的换热规律；计算结果与相关文献进行对比，验证转子温度场计算方法的可行性。计算结果表明：从慢车到最大状态过程中，高压压气机盘最大径向温差先增加后减小直至稳定，中心孔附近较厚区域温度梯度最大；低压涡轮盘中下部沿轴向盘面温差很小，整个轮盘高温区域集中在轮盘盘缘。%In order to obtain the temperature field data for low cycle fatigue life predictions of compressor and turbine disc, the 3-dimensional transient temperature field of a high pressure（HP） compressor disc and steady temperature field of a low pressure（LP） turbine disc are calculated utilizing the thermal analysis module of AN- SYS. The thermal boundary conditions of the rotating cavity, rotor string, seal labyrinth, fir-tree connection are analyzed and discussed. The numerical results are compared with the related literature and the feasibility of numerical method is analyzed. The results indicate that, from idling rating to maximum rating, the radial tern perature difference is firstly increased, and then decreased gradually till to a steady value; the thick region near the centevhole of disc is suffered from the condition of maximum temperature gradient; for the LP turbine disc, the temperature difference between the fore-and after-ward surface is low, and the high temperature region are mostly located at disc rim.
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