Numerical simulation of stall inception in single-stage axial-flow compressor

Based on the investigation results involving pre-stall behavior in subsonic single-stage axial-flow compressor test rig under isolated-rotor environment, whole-passage simulations were further carried out to investigate the stall inception process under single-stage environment. The monitoring results from the numerical probes indicate that the local breakdown of flow-field of single-stage axial-flow compressor is initiated at rotor tip region during stall inception process. The simulation results were validated by available experimental data. Detailed instantaneous flow-field analysis demonstrates that the type of pre-stall wave is multi-cell disturbance under single-stage environment in contrast to spike disturbance under isolated-rotor environment, implying that the presence of stator alters the pattern of near-tip circumferential loading distribution. However, the flow mechanism for the emergence of multi-cell disturbance is still represented by the formation and movement of tip secondary vortex.