Experimental Study of Casing Boundary Layers in a Multistage Axial Compressor

[+] Author and Article Information
S. Venkateswaran

Fluid/Thermal Research, Lockheed Engineering and Science Co., Hampton, VA 23666

J. Fluids Eng 113(2), 240-244 (Jun 01, 1991) (5 pages) doi:10.1115/1.2909486 History: Received September 14, 1988; Online May 23, 2008


Measurements of the casing boundary layers were obtained in a four-stage, low speed axial flow compressor, to verify the ‘law of the wall’ applicability to these complex flows. Some of the available shear stress models of the two-dimensional flows have been examined towards the quantitative assessment of skin friction. The shear stress prediction obtained from the Ludwieg-Tillmann relation applied to the streamwise or untwisted profile agreed closely with the measured shear stress by the hot wire. The skin friction was fairly constant for rotor and stator flows and was close to the flat plate values. The boundary layer profiles exhibited a well pronounced semi-logarithmic region with the universal constants of the law of the wall far removed from the standard two dimensional values, especially for rotor flows. Stator flows showed signs of similarity to two dimensional flows.

Copyright © 1991 by The American Society of Mechanical Engineers
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