Wall Boundary Layer Development Near the Tip Region of an IGV of an Axial Flow Compressor

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

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

J. Eng. Gas Turbines Power 106(2), 337-345 (Apr 01, 1984) (9 pages) doi:10.1115/1.3239570 History: Received December 27, 1982; Online October 15, 2009


The annulus wall boundary layer inside the blade passage of the inlet guide vane (IGV) passage of a low-speed axial compressor stage was measured with a miniature five-hole probe. The three-dimensional velocity and pressure fields were measured at various axial and tangential locations. Limiting streamline angles and static pressures were also measured on the casing of the IGV passage. Strong secondary vorticity was developed. The data were analyzed and correlated with the existing velocity profile correlations. The end wall losses were also derived from these data.

Copyright © 1984 by ASME
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