An accurate and efficient numerical method was developed for aeroelastic analysis of turbomachinery blading in unsteady transonic flows. The unsteady Reynolds-averaged Navier-Stokes equation with Spalart-Allmaras turbulence model was solved with an implicit dual-time stepping technique. The blade passages were discretised using finite volume method with multi-block. The unsteady aerodynamic responses and the aeroelastic stability of the 10th standard configuration undergoing bending blade vibration were calculated in subsonic and transonic flows. The effects of flow conditions, reduced frequency and inter-blade phase angle on cascade aeroelastic stability were analyzed. The results indicate that the shock destabilizes the cascade and the influence of inter-blade phase angle is enforced under higher reduced frequency.%发展并验证了一种适用于叶轮机内部非定常跨音流动诱导的叶片气弹问题的高效、准确的数值模拟方法.采用有限体积的多块结构化网格形式,多重网格方法加速收敛,隐式的双时间步时间推进,Spalart- Allmaras(S- A)湍流模型求解非定常雷诺平均Navier- Stokes方程.通过气动弹性标准算例10,叶片在高亚音和跨音流动下做弯曲振动,分析了流动状态、折合频率以及叶片间相位角对叶片表面非定常气动力响应以及叶栅气弹稳定性的影响.分析结果表明激波在此跨音振荡压气机叶栅中起失稳作用,叶片间相位角对气弹稳定性的影响在高折合频率下被加强.
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