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.
079184241X
1875-1885
The American Society of Mechanical Engineers
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
15 October 2006
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.
(2006)
The effect of wake induced structures on compressor boundary-layers.
In ASME Turbo Expo 2006: Power for Land, Sea, and Air. Volume 6: Turbomachinery, Parts A and B.
The American Society of Mechanical Engineers.
.
(doi:10.1115/GT2006-90892).
Record type:
Conference or Workshop Item
(Paper)
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.
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Published date: 15 October 2006
Venue - Dates:
ASME Turbo Expo 2006: Power for Land, Sea and Air, Barcelona, Spain, 2006-05-08 - 2006-05-11
Organisations:
Aerodynamics & Flight Mechanics Group
Identifiers
Local EPrints ID: 334488
URI: http://eprints.soton.ac.uk/id/eprint/334488
ISBN: 079184241X
PURE UUID: aa5ecb1a-589a-40d1-b461-2350e46827f2
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Date deposited: 13 Mar 2012 17:07
Last modified: 14 Mar 2024 10:35
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Contributors
Author:
Andrew P.S. Wheeler
Author:
Robert J. Miller
Author:
Howard P. Hodson
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