涡轮导向叶片热冲击双向耦合数值研究

航空发动机涡轮导向叶片热冲击过程是一个典型的固体变形场、温度场和流场三场耦合作用问题,工况复杂。基于流固热耦合理论,求解一维平板模型热弹性解析解;并进行数值模拟和对比分析,验证了双向耦合方法的有效性。应用建立的双向耦合方法对某涡轮导向叶片热冲击过程进行数值模拟,得到了涡轮导向叶片表面温度及热应力分布规律。研究表明,提出的双向耦合方法可以有效地预测涡轮导向叶片的温度及应力分布规律,计算温度与试验误差小于5%;应力集中处与试验中叶片破坏区域一致。研究对航空发动机涡轮叶片热冲击过程数值模拟提供了有效方法。

Numerical Simulation of Turbo Guide Vanes Subjected to Thermal Shock Load Using Bidirectional Coupling Method

The thermal shock of aero-engine vanes is a typical problem of the thermo-structural-fluid coupling action. By contrasting the analytical solution of one-dimensional slab model with the results of simulation, they are basically in accordance, which confirm the effectiveness of the bidirectional coupling method. The surface temperature field and distribution law of thermal stresses of turbine vane were evaluated withnumerical calculation on the basis of thermal-shock model according to bidirectional coupling method. This study shows that establish the bidirectional coupling method can predict the surface temperature field and distribution law of thermal stresses of turbine vane effectively. Compared the calculated data with the experiment, the temperature error is less than 5%, the stress concentration sites consist with the blade failure area. The research provided an effective method to numerical simulate the thermal-shock problems of aero-engine turbo blade.