A Computational Method of Rotating Stall and Surge Transients in Axial Compressor

The onset of rotating stall and surge in compressors limits the operating range aero-engines. Accurately predicting key features during these events is critical engine design process. In this paper, a three-dimensional computational model for transient simulation multi-stage axial proposed. kinetic equations describing dynamic process compression system are constructed, with 3D through-flow part 1D gas collector outlet part. calculation source term performed using developed body-force model, which realizes correlation between deviation angle loss coefficient inlet parameters various flow regions. Validated on single-stage compressor single-rotor fan, results show that method capable capturing correctly structure cell can be captured. addition, could used analysis load, significant structural integrity compressor.