A generalized flat plate cascade model is developed in this study to predict the unsteady aerodynamics of a blade row with circumferentially non-uniform spacing in subsonic compressible flow. With no constrains on symmetry, this model can be applied to a blade row with any user specified non-uniform spacing pattern. The effect of non-uniform 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 non-uniform blade spacing can greatly alter the blade unsteady loading and spread the acoustic energy to a broader frequency range.
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