Compressor wake/leading-edge interactions at off design incidences
Compressor wake/leading-edge interactions at off design incidences
In this paper, the effects of wake/leading-edge interactions were studied at off-design conditions. Measurements were performed on the stator-blade suction surface at midspan. The leading-edge flow-field was investigated using hotwire micro-traverses, hotfilm surface shear-stress sensors and pressure micro-tappings. The trailing-edge flow-field was investigated using hotwire boundary-layer traverses. Unsteady CFD calculations were also performed to aid the interpretation of the results. At low flow coefficients, the time-averaged momentum thickness of the leading-edge boundary layer was found to rise as the flow coefficient was reduced. The time-resolved momentum-thickness rose due to the interaction of the incoming rotor wake. As the flow coefficient was reduced, the incoming wakes increased in pitch-wise extent, velocity deficit and turbulence intensity. This increased both the time-resolved rise in the momentum thickness and the turbulent spot production within the wake affected boundary-layer. Close to stall, a drop in the leading-edge momentum thickness was observed in-between wake events. This was associated with the formation of a leading-edge separation bubble in-between wake events. The wake interaction with the bubble gave rise to a shedding phenomenon, which produced large length scale disturbances in the surface shear stress
978-0-7918-4316-1
1795-1806
The American Society of Mechanical Engineers
Wheeler, Andrew P.S.
0f243ba3-3aae-470c-ba4a-46a8c4b9197a
Miller, Robert J.
c0b73cf1-ba94-4018-ba7a-dc471ffa6d76
2008
Wheeler, Andrew P.S.
0f243ba3-3aae-470c-ba4a-46a8c4b9197a
Miller, Robert J.
c0b73cf1-ba94-4018-ba7a-dc471ffa6d76
Wheeler, Andrew P.S. and Miller, Robert J.
(2008)
Compressor wake/leading-edge interactions at off design incidences.
In Proceedings of ASME Turbo Expo 2008: Power for Land, Sea, and Air (GT2008). Turbomachinery, Parts A, B, and C.
The American Society of Mechanical Engineers.
.
(doi:10.1115/GT2008-50177).
Record type:
Conference or Workshop Item
(Paper)
Abstract
In this paper, the effects of wake/leading-edge interactions were studied at off-design conditions. Measurements were performed on the stator-blade suction surface at midspan. The leading-edge flow-field was investigated using hotwire micro-traverses, hotfilm surface shear-stress sensors and pressure micro-tappings. The trailing-edge flow-field was investigated using hotwire boundary-layer traverses. Unsteady CFD calculations were also performed to aid the interpretation of the results. At low flow coefficients, the time-averaged momentum thickness of the leading-edge boundary layer was found to rise as the flow coefficient was reduced. The time-resolved momentum-thickness rose due to the interaction of the incoming rotor wake. As the flow coefficient was reduced, the incoming wakes increased in pitch-wise extent, velocity deficit and turbulence intensity. This increased both the time-resolved rise in the momentum thickness and the turbulent spot production within the wake affected boundary-layer. Close to stall, a drop in the leading-edge momentum thickness was observed in-between wake events. This was associated with the formation of a leading-edge separation bubble in-between wake events. The wake interaction with the bubble gave rise to a shedding phenomenon, which produced large length scale disturbances in the surface shear stress
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Published date: 2008
Venue - Dates:
ASME Turbo Expo 2008: Power for Land, Sea, and Air (GT2008), Berlin, Germany, 2008-06-09 - 2008-06-13
Organisations:
Aerodynamics & Flight Mechanics Group
Identifiers
Local EPrints ID: 334484
URI: http://eprints.soton.ac.uk/id/eprint/334484
ISBN: 978-0-7918-4316-1
PURE UUID: 380ee8d7-2b63-49ec-a47b-7d672dbabaa3
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Date deposited: 09 Mar 2012 08:23
Last modified: 14 Mar 2024 10:35
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Author:
Andrew P.S. Wheeler
Author:
Robert J. Miller
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