摘要
采用CFD技术,引入等叶片间相位角假设,运用非耦合的能量法,研究了典型叶轮机叶片的颤振特性。采用有限体积法求解NS方程,运用SST湍流模型,通过恒定叶间相位角简化叶轮机流场,计算了NASA Rotor67和STCF4(the Fourth Standard Configuration)的振动叶片的流场特性。计算表明:转子67采用碳钢材料时,在效率峰值的工况下,叶片不会发生颤振;而STCF4在一阶弯曲振动中会出现不稳定;叶间相位角(IBPA)对振动叶片的气动弹性稳定性有明显的影响。
Flutter calculations for turbomachinery blade rows often employ the energy method and Lane＇s traveling wave model in which the adjacent blades in a blade row are assumed to vibrate at the same frequency but with a constant phase difference, called interblade phase angle （IBPA）. With this model, aerodynamic responses of the blade row can be determined by using a single blade passage to minimize the computational effort. Consequently, a phase- shifted periodic boundary condition has to be applied when the IBPA is not zero. Compared with the experiments results of NASA Rotor67 and the fourth standard configuration （STCF4）, the unsteady aerodynamics and aeroelastic behaviors are described, and the flutter predictions are performed according to the damping coefficient based on the energy method.
出处
《航空计算技术》
2009年第4期75-78,共4页
Aeronautical Computing Technique
