压气机转子叶片颤振边界的预测方法

通过发展的基于能量法的颤振数值预测方法得到了压气机转子叶片的颤振边界.将计算结构动力学(CSD)分析得到的叶片表面节点位移插值到耦合面的流体网格点上,并将设计的多层动网格技术应用于计算流体动力学(CFD)方法,实现叶栅振荡作用下的非定常分析,得到叶片表面的非定常气动功以及模态气动阻尼比.以某第一级压气机转子叶片为例,对...

Prediction method of blade flutter boundary in a compressor stage

The blade flutter boundary in a compressor stage was obtained by the developed numerical prediction method based on the energy method.The displacements of blade surface structural nodes,obtained from the computational structural dynamics (CSD) analysis,were transferred to fluid interface grids,and the designed multi-layer moving grid technique was applied to computational fluid dynamics (CFD).The unsteady analysis under the oscillating cascades was achieved to calculate the unsteady aerodynamic work for aerodynamic modal damping ratio.For a certain first-stage compressor rotor,the aeroelastic stability of different operating conditions was investigated and compared at different blade modes.And the blade flutter boundary has been obtained by analyzing the distribution of aerodynamic modal damping ratio in compressor characteristic map.The results show that the developed numerical method for aerodynamic modal damping ratio to determine the flutter boundary is feasible to preliminarily predict the aeroelastic stability of compressor blade.