Exploration of Flow Instability Characteristics in a Two-Stage Axial-Flow Compressor via Numerical Simulation Method

A four-blade-passage numerical model was developed for a two-stage axial-flow compressor with an inlet guide vane (IGV) the purpose of studying steady and dynamic characteristics approaching its stability limit. The flow-field information indicated that tip-leakage flow decreased more rapidly from blade’s leading edge to trailing edge, decreasing rate. leakage verified be driven via blade load over whole operating range. Further research on carried out. magnitude highest in leading-edge portion first-stage rotor determined lowest rate steady-simulation analysis. circumferential grooves improved rotor’s stable range reducing load. Unsteady-simulation results showed extreme appeared first at front stage, second stage played positive compensative role through releasing some stage. It can generalized specific speed is not only any single but also other stages multistage compressor.