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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,对比了不同振型、不同工况下的气动弹性稳定性,并最终在压气机转子特性图上给出了叶片的失速颤振边界.计算结果表明:所发展的数值预测方法可以用于分析压气机叶片的气动弹性稳定性,并通过模态气动阻尼比能够较好地给出压气机叶片的颤振边界.
The flutter boundary of the compressor rotor blade is obtained through the development of the flutter numerical prediction method based on the energy method. The displacement of the vane surface node calculated by the computational structural dynamics (CSD) is interpolated to the fluid grid point of the coupling surface The multi-layer moving mesh technology is applied to the computational fluid dynamics (CFD) method to realize unsteady analysis under the action of cascade vibration, and the unsteady aerodynamic work and modal aerodynamic damping ratio of the blade surface are obtained. Stage compressor rotor blade is taken as an example to compare the aerodynamic stability under different conditions and different conditions, and finally the stall flutter boundary of the blade is given on the compressor rotor characteristic diagram.The calculation results show that the developed The numerical prediction method can be used to analyze the aeroelastic stability of the compressor blades. The modal aerodynamic damping ratio can give a good indication of the flutter boundary of the compressor blades.