The effect of wake induced structures on compressor boundary-layers
The effect of wake induced structures on compressor boundary-layers
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.
compressors, boundary layer turbulence, laminar to turbulent transitions, flow visualisation, computational fluid dynamics, wakes, blades
705-712
Wheeler, Andrew P.S.
0f243ba3-3aae-470c-ba4a-46a8c4b9197a
Miller, Robert J.
c0b73cf1-ba94-4018-ba7a-dc471ffa6d76
Hodson, Howard P.
30aacb20-0fed-4e0f-8178-3fd7f4618632
October 2007
Wheeler, Andrew P.S.
0f243ba3-3aae-470c-ba4a-46a8c4b9197a
Miller, Robert J.
c0b73cf1-ba94-4018-ba7a-dc471ffa6d76
Hodson, Howard P.
30aacb20-0fed-4e0f-8178-3fd7f4618632
Wheeler, Andrew P.S., Miller, Robert J. and Hodson, Howard P.
(2007)
The effect of wake induced structures on compressor boundary-layers.
Journal of Turbomachinery, 129 (4), .
(doi:10.1115/1.2720499).
Abstract
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.
This record has no associated files available for download.
More information
Published date: October 2007
Keywords:
compressors, boundary layer turbulence, laminar to turbulent transitions, flow visualisation, computational fluid dynamics, wakes, blades
Organisations:
Aerodynamics & Flight Mechanics Group
Identifiers
Local EPrints ID: 334478
URI: http://eprints.soton.ac.uk/id/eprint/334478
ISSN: 0889-504X
PURE UUID: 12424250-32cf-4595-bb84-a28fe35b1a50
Catalogue record
Date deposited: 09 Mar 2012 13:34
Last modified: 14 Mar 2024 10:35
Export record
Altmetrics
Contributors
Author:
Andrew P.S. Wheeler
Author:
Robert J. Miller
Author:
Howard P. Hodson
Download statistics
Downloads from ePrints over the past year. Other digital versions may also be available to download e.g. from the publisher's website.
View more statistics