Interaction of Compressor Rotor Blade Wake With Wall Boundary Layer/Vortex in the End-Wall Region

[+] Author and Article Information
B. Lakshminarayana, A. Ravindranath

Department of Aerospace Engineering, The Pennsylvania State University, University Park, Penn. 16802

J. Eng. Power 104(2), 467-478 (Apr 01, 1982) (12 pages) doi:10.1115/1.3227302 History: Received April 01, 1981; Online September 28, 2009


This paper reports the experimental study of the three-dimensional characteristics of the mean velocity of the rotor wake inside the annulus- and hub-wall boundary layers. The measurements were taken with a rotating three-sensor hot wire behind the rotor. This set of measurements probably represents the first set of comprehensive measurements taken inside the annulus- and hub-wall boundary layers. The wake was surveyed at several radial locations inside the boundary layer region and at several axial locations. Interaction of the wake with the annulus-wall boundary layer, secondary flow, tip-leakage flow, and the trailing vortex system results in slower decay and larger width of the wake. The presence of a strong vortex and its merger with the wake is also observed. The end-wall boundary layers and the secondary flow were found to have a substantial effect on both the decay characteristics and the profile of the wake. These and other measurements are reported and interpreted in this paper.

Copyright © 1982 by ASME
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