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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 provide the temperature field data for low cycle fatigue life analysis of compressor disk and turbine disk, the transient temperature field of aeroengine high-pressure compressor rotor and the three-dimensional steady-state temperature field of low-pressure turbine rotor are calculated by the thermal analysis module of ANSYS software. the study. The heat transfer laws of the rotating disk cavity, the rotating shaft system, the sealing labyrinth teeth and the tenon assembly gap are analyzed emphatically. The calculation results are compared with the related literatures to verify the feasibility of the rotor temperature field calculation method. The calculation results show that the maximum radial temperature difference of the high-pressure compressor disk first increases and then decreases until it reaches a steady state, and the temperature gradient in the thicker area near the center hole is the largest. In the middle and lower parts of the low-pressure turbine disk, the temperature difference along the axial disk surface is small , The entire roulette high temperature area concentrated in the roulette rim.