Numerical Simulation of the Rotating Stall Feature on a Single Stage Transonic Compressor

To study the characteristics of stall inception and stall development in multi-row transonic axial compressor, taking NASA Stage 35 as an example, the development from near stall to fully developed stall was simulated. The simulation was conducted based on the in-house code ASPAC. The dynamic overlapped grid technique, mass flow boundary at the outlet, throttle valve boundary condition were used. The simulation result indicates that: the developed simulation technique can predict the development process of rotating stall correctly. Under the condition of uniform inlet flow, as the flow approaches to stall condition, the blade tip leakage occurs on the leading edge of pressure surface for some rotors, which leads to the rotating stall of the compressor. Under the condition of stall inception, circumferential non-uniform flow occurs and propagates circumferentially. When the rotating stall is fully developed, the adverse flow occurs on the pressure surface of stator and is mainly adjacent to the stall cells in the rotor, meanwhile the flow structure in the stall region nearly does not change with time.