Application of nonaxisymmetric casing treatments (CTs) can extend the operating range of a transonic compressor significantly. Recent CT designs have proven successful at achieving operating range extension without efficiency loss under design conditions. Two different CT designs were investigated on a high-speed one and a half stage test rig using extensive instrumentation. The stage setup is representative of the front stage of a modern high-pressure compressor. Results of particle image velocimetry (PIV) measurements taken in the blade tip region underneath the CT show a significantly modified flow structure compared to the smooth casing reference case. Blockage zone, secondary flow, and shock structures are affected by the CT, especially in highly throttled operating conditions. The stall inception process of the system with axial slots shows unexpected behavior, with modal activities that are not observed without CT. These activities are resolved using unsteady wall pressure (WP) and hot wire measurements.

Issue Section:
Research Papers
Keywords:
Aeromechanical instabilities, Cavity flows, Fan, Measurement techniques, Compressor stall, Surge, Turbine aerodynamic design, Compressor , Leaking flows, Operability
Topics:
Blades, Compressors, Design, Flow (Dynamics), Rotors, Shock (Mechanics), Stall inception, Pressure

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