Study on Surge and Rotating Stall in Axial Compressors : A Numerical Model and Parametric Study for Multiblade-Row Compressors

Abstract

This study investigates the effects of various parameters on the inception and post-stall characteristics of surge and rotating stall in multistage axial compressors, using a numerical model for multiblade-row compressors. The parameters described in this study are the shape of the total pressure loss and deviation angle characteristics, IGV (inlet guide vane) outlet flow angle, inlet flow distortion, and bleeding. It is found that there are two types of rotating stall differing in magnitude, that inlet distortion and the deterioration in compressor performance reduce the inception margin of unstable behavior, and that there is an optimal bleeding that can optimize the inception margin of unstable behavior. The usefulness of the present model is examined through numerical investigations, and the validity of the model is confirmed by comparing predicted results obtained using the model with test results obtained using a single-stage compressor and a 3-stage compressor.