叶间相位角对叶片颤振的影响

发展了一种基于能量法并计及叶间相位角(IBPA)影响的数值计算方法.建立了全环振荡叶栅模型,将每一个扇区分为叶片表面附近的可动域及其外围的固定域,采用有限元形函数将计算结构动力学(CSD)网格点位移的传递到计算流体动力学(CFD)的耦合面网格点上,求解了全环振荡叶栅由k-ε湍流模型封闭的Reynolds平均Navier-Stokes(RANS)方程.以NASA 67转子叶片为例,在设计转速下,基于能量法分析了叶间相位角对叶片颤振的影响.计算结果表明:叶间相位角对叶片颤振有显著影响.

Influence of interblade phase angle on the flutter of rotor blades

A numerical simulation method in turbomachinery bladings basing on energy method with Interblade Phase Angle (IBPA) has been developed. The whole annular oscillating cascades have been modeled with each blade channel divided into the moveable region near the blade surface and the outer fixed region. The node displacements of finite element model, on the basis of Computational Structural Dynamics (CSD), have been transferred to fluid interface grids with finite element interpolation algorithm. Reynolds-averaged Navier-Stokes (RANS) equations with turbulence models for closure have been solved for the whole annular oscillating cascades. At the design speed of NASA Rotor 67, the aerodynamic work in one oscillating period and the corresponding aerodynamic modal damping ratios of the whole annular cascades in different IBPA are obtained. The effects of IBPA on the flutter of cascades have been determined on the basis of energy method. The results show that IBPA has significant influence on the flutter of rotor blades.