End-wall and profile losses in a low-speed axial flow compressor rotorThe 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.
Document ID
19860037352
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Lakshminarayana, B. (Pennsylvania State Univ. University Park, PA, United States)
Sitaram, N. (Pennsylvania State Univ. University Park, PA, United States)
Zhang, J. (Pennsylvania State University University Park, PA, United States)