Nonuniform Flow in a High Speed Compressor Due to Asymmetric Tip Clearance

Abstract

This paper presents an analytical model to predict flow response in a high speed compressor stage caused by asymmetric tip clearance distribution. The model assumes inviscid, compressible flow, and uses basic conservation equations. The stage is modelled as an actuator disc, and the analysis is done in the meridional and radial planes. First, an axisymmetric meridional flow model for tip clearance and passage flows is developed. The model takes into consideration the detached shock that occurs in the rotor passage at the design point. This shock model is used to calculate the change in flow variables. Then, this model is perturbed to obtain non-axisymmetric flow quantities in the radial plane.