Abstract
This paper addresses off-design unsteady aerodynamics including dynamic stall due to the interaction of rotor-generated wakes with a downstream vane row. This is accomplished by obtaining detailed rotor-stator unsteady aerodynamic blade row interaction data in a low-speed axial-flow research compressor. Experiments directed at time- variant PIV measurements of the downstream stator flow field at negative incidence angles typical of part speed operation of the later stages of a high-pressure compressor are described. Two stator stagger angles are investigated. A stator stagger angle of -17° provides a classic dynamic stall condition. At a more negative stagger of -22°, a steady separation is modulated by the wake pass event and also results in a shed vortex structure. The generation and subsequent shedding of the dynamic stall vortex is accompanied by flow separation and reattachment as a rotor traverses the stator passage.
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