The boundary layer on an axial-flow compressor stator blade has been measured using an ensemble-averaging technique. Although the mean velocity profiles appear to indicate fully developed turbulent flow, ensemble-averaged instantaneous profiles show the boundary layer to be highly unsteady and transitional over much of the blade chord. At a given chordwise position, variations in boundary-layer thickness with time of up to 150 percent were recorded. When compared to boundary-layer development on a similar blade in a two-dimensional cascade the stator blade boundary-layer growth was found to be much greater. The results indicate that extreme caution should be used in attempting to predict blade boundary-layer development from cascade test results or steady calculation procedures.
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April 1978
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Journal of Engineering for Power
Research Papers
Boundary-Layer Development on an Axial-Flow Compressor Stator Blade
R. L. Evans
R. L. Evans
Department of Mechanical Engineering, University of Toronto, Toronto, Canada
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R. L. Evans
Department of Mechanical Engineering, University of Toronto, Toronto, Canada
J. Eng. Power. Apr 1978, 100(2): 287-292 (6 pages)
Published Online: April 1, 1978
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Received:
December 7, 1976
Online:
July 14, 2010
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Evans, R. L. (April 1, 1978). "Boundary-Layer Development on an Axial-Flow Compressor Stator Blade." ASME. J. Eng. Power. April 1978; 100(2): 287–292. https://doi.org/10.1115/1.3446346
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