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.