Investigation of the casing groove location effect for a large tip clearance in a counter-rotating axial flow compressor
Author:
Funder
National Natural Science Foundation of China
Collaborative Innovation Center of Advanced Aero-Engine in Beijing
Hong Kong Scholars Program
Publisher
Elsevier BV
Subject
Aerospace Engineering
Reference46 articles.
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2. A study of spike and modal stall phenomena in a low-speed axial compressor;Camp;J. Turbomach.,1998
3. The influence of tip clearance momentum flux on stall inception in a high-speed axial compressor;Cameron;J. Turbomach.,2013
4. Numerical investigation into the underlying mechanism connecting the vortex breakdown to the flow unsteadiness in a transonic compressor rotor;Wu;Aerosp. Sci. Technol.,2019
5. Circumferentially propagating characteristic dominated by unsteady tip leakage flow in axial flow compressors;Li;Aerosp. Sci. Technol.,2019
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