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.


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    Title :

    Effects of Nonuniform Blade Spacing on Compressor Rotor Forced Response and Aeroacoustics


    Contributors:

    Published in:

    Publication date :

    2020-09-01




    Type of media :

    Conference paper , Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English