Prediction of stall inception in multi-stage compressors based on an eigenvalue approach

Abstract

A stability model for multi-stage compressor is developed on the basis of the eigenvalue approach. This model assumes that the unsteady flow field can be decomposed into pressure, vortex and entropy waves. Besides, a linear cascade of blades is modeled by three-dimensional semi-actuator disk theory and the characteristics of steady flow field are also considered in the present model. The connection between the analytical solution for stator, rotor and gap can be established by applying mode matching approach, the relevant stability equation can be expressed in the form of matrix, while the compressor system stability can be judged by the imaginary part of the matrix eigenvalue. The capacity of the stall inception model to predict the stall inception point of multi-stage compressor is assessed against the experimental data of National Aeronautics and Space Administration (NASA) two stage fan. The theoretical results show that this model can predict the stall onset points of a two-stage fan at different operating speeds with a reasonable accuracy.