Characterization of the tip leakage vortex and corner separation in a compressor cascade at near-stall conditions

Abstract

The unsteady dynamics of secondary flows in axial compressors, such as tip leakage vortices (TLVs) and corner separations (CS), are significant contributors to aerodynamic losses and instabilities, particularly under off-design conditions near the stall margin. Through high-fidelity wall-resolving large eddy simulations (WRLES) of an annular, rotating compressor cascade with a large tip clearance at design and near stall conditions the changes in flow dynamics taking place near stall will be evidenced. Modal analysis will identify coherent structures and their dynamics, providing insight into TLV breakdown, vortex migration, and lowfrequency oscillations

Postprint (published version)