A generalized flat plate cascade model is developed in this study to predict the unsteady aerodynamics of a blade row with circumferentially nonuniform spacing in subsonic compressible flow. With no constraints on symmetry, this model can be applied to a blade row with any user-specified nonuniform blade spacing pattern. The effect of nonuniform blade spacing on compressor rotor forced response and aeroacoustic behavior is demonstrated by applying this model to case studies based on the geometry and flow conditions of the Purdue 3-Stage Axial Compressor. The results show that nonuniform blade spacing can greatly alter the blade unsteady loading and spread the acoustic energy to a broader frequency range.

在这项研究中开发了一个通用的平板级联模型，以预测在亚音速可压缩流中具有周向不均匀间隔的叶片行的不稳定空气动力学。在没有对称性约束的情况下，该模型可以应用于具有任何用户指定的非均匀叶片间距模式的叶片排。通过将此模型应用于基于Purdue 3级轴流式压缩机的几何形状和流动条件的案例研究，可以证明叶片间距不均匀对压缩机转子的强迫响应和空气声学特性的影响。结果表明，不均匀的叶片间距可以极大地改变叶片的非稳态载荷，并将声能扩展到更宽的频率范围。