NUMERICAL STUDY OF STALL INCEPTION IN A TRANSONIC AXIAL COMPRESSOR ROTOR BASED ON THE THROTTLE MODEL

The goal of the current paper is to investigate inner flow behavior on stall inception in a
transonic compressor rotor. The stall inception process is numerically carried out by unste-
ady 3-D simulations based on the throttle model. The current study shows that stall starts
from the tip of the blade, and stall cell extends to the axial, circumferential and radial
directions. Through the comparison of flow transition characteristics at different flow rate
conditions, the interface between the incoming flow and tip clearance flow shifts forward
to the upstream as the mass flow decreases. Eventually, the shock detaches from the blade
leading edge, and tip clearance flow spills into the adjacent blade passage, thus stall happens
in the affected blade passages.