Stall Inception Prediction of Transonic Compressor with Wire Mesh Casing Treatment

Abstract

A wire mesh casing treatment is proposed and numerically tested on the transonic axial compressor (Rotor 37). A theoretical stall inception prediction model was developed to account for the wire mesh casing treatment, which was modeled as an impedance boundary condition. This model was validated on a low-speed compressor, replicating the experimental trend with reliable precision. The impedance boundary condition effectively attenuates disturbances and confines the distribution range of perturbations compared to the solid wall boundary condition. Furthermore, the installation of the wire mesh casing treatment induced a downstream shift in the passage shock wave and enhanced the flow capacity in the blade tip region. The effects of the casing treatment on different installation locations were investigated, and the results indicated that the maximum stall margin improvement occurred when the casing treatment was positioned at the midchord location. The integrated design of the casing treatment and blade profile, along with the established prediction model, is also discussed. This model demonstrates reliable precision when compared to the experimental results and addresses the need for rapid design iteration during the initial design phase.