End-Wall and Profile Losses in a Low-Speed Axial Flow Compressor Rotor

[+] Author and Article Information
B. Lakshminarayana, N. Sitaram, J. Zhang

Department of Aerospace Engineering, The Pennsylvania State University, University Park, PA 16802

J. Eng. Gas Turbines Power 108(1), 22-31 (Jan 01, 1986) (10 pages) doi:10.1115/1.3239880 History: Received January 10, 1985; Online October 15, 2009


The blade-to-blade variation of relative stagnation pressure losses in the tip region inside the rotor of a single-stage, axial-flow compressor is presented and interpreted in this paper. The losses are measured at two flow coefficients (one at the design point and the other at the near peak pressure rise point) to discern the effect of blade loading on the end-wall losses. The tip clearance losses are found to increase with an increase in the pressure rise coefficient. The losses away from the tip region and near the hub regions are measured downstream. The losses are integrated and interpreted in this paper.

Copyright © 1986 by ASME
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