Effects of Nonuniform Blade Spacing on Compressor Rotor Forced Response and Aeroacoustics
Yujun Leng, Nicole L. Key
Abstract
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.
Topics & Concepts
Gas compressorBlade (archaeology)AerodynamicsRotor (electric)CascadeMechanicsAeroacousticsAxial compressorCompressible flowStructural engineeringHelicopter rotorCompressibilityAcousticsEngineeringPhysicsAerospace engineeringSound pressureMechanical engineeringChemical engineeringTurbomachinery Performance and OptimizationBladed Disk Vibration DynamicsAerodynamics and Acoustics in Jet Flows