The interaction of a convected wake with a compressor blade boundary layer was investigated. Measurements within a single-stage compressor were made using an endoscopic PIV system, a surface mounted pressure transducer, hotfilms and hotwire traverses, along with CFD simulations. The wake/leading-edge interaction was shown to lead to the formation of a thickened laminar boundary-layer, within which turbulent spots formed close to the leading edge. The thickened boundary-layer became turbulent and propagated down the blade surface, giving rise to pressure perturbations of 7% of the inlet dynamic head in magnitude. The results indicate that wake/leading-edge interactions have a crucial role to play in the performance of compressor blades in the presence of wakes.
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October 2007
Research Papers
The Effect of Wake Induced Structures on Compressor Boundary-Layers
Andrew P. S. Wheeler,
Andrew P. S. Wheeler
Whittle Laboratory,
University of Cambridge
, Cambridge, UK
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Robert J. Miller,
Robert J. Miller
Whittle Laboratory,
University of Cambridge
, Cambridge, UK
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Howard P. Hodson
Howard P. Hodson
Whittle Laboratory,
University of Cambridge
, Cambridge, UK
Search for other works by this author on:
Andrew P. S. Wheeler
Whittle Laboratory,
University of Cambridge
, Cambridge, UK
Robert J. Miller
Whittle Laboratory,
University of Cambridge
, Cambridge, UK
Howard P. Hodson
Whittle Laboratory,
University of Cambridge
, Cambridge, UKJ. Turbomach. Oct 2007, 129(4): 705-712 (8 pages)
Published Online: July 31, 2006
Article history
Revised:
July 31, 2006
Received:
July 31, 2006
Citation
Wheeler, A. P. S., Miller, R. J., and Hodson, H. P. (July 31, 2006). "The Effect of Wake Induced Structures on Compressor Boundary-Layers." ASME. J. Turbomach. October 2007; 129(4): 705–712. https://doi.org/10.1115/1.2720499
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