Influence of Blade Tip Surface Roughness on the Performance of a Single-Stage Axial Flow Compressor

Kodancha, Pradyumna and Salunkhe, Pramod (2021) Influence of Blade Tip Surface Roughness on the Performance of a Single-Stage Axial Flow Compressor. Journal of Fluids Engineering, Transactions of the ASME, 143. ISSN 0098-2202

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Abstract

Numerical investigations are carried out in a single-stage subsonic axial flow compressor to unravel the influence of blade tip surface roughness on the tip leakage flow character�istics and hence the compressor performance. The studies were carried out at different tip clearance of 0.38s, 0.77s, 1.15s, and 1.54s and blade tip surface roughness of 0.31e and 0.62e. The tip clearance of 0.38s with blade tip surface roughness of 0.62e resulted in the highest stall margin and pressure rise of 20.3% and 4.3%, respectively. The com�pressor blade loading was found to be improved by 5.9% after incorporating the blade tip surface roughness. The isosurfaces of vorticity contour plotted using the Q-criterion showed the reduction in strength of the tip leakage vortex. The tip leakage trajectory was found to be shifted toward the suction surface of the blade for the blade tip with surface roughness. This positive alteration in the tip leakage flow structure led to the improved performance for the blade tip with surface roughness.

Item Type: Article
Uncontrolled Keywords: axial compressor, flow instability, stall margin, tip clearance, performance characteristics
Subjects: Engineering > MIT Manipal > Aeronautical and Automobile
Depositing User: MIT Library
Date Deposited: 25 Aug 2021 09:22
Last Modified: 25 Aug 2021 09:22
URI: http://eprints.manipal.edu/id/eprint/157182

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