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An experimental study on the effects of tip clearance on flow field and losses in an axial flow compressor rotorDetailed measurement of the flow field in the tip region of a compressor rotor was carried out using a Laser Doppler Velocimeter (LDV) and a Kiel probe at two different tip clearance heights. At both clearance sizes, the relative stagnation pressure and the axial and tangential components of relative velocities were measured upstream, inside the passage and downstream of the rotor, up to about 20 percent of the blade span from the annulus wall. The velocities, outlet angles, losses, momentum thickness, and force defect thickness are compared for the two clearances. A detailed interpretation of the effect of tip clearance on the flow field is given. There are substantial differences in flow field, on momentum thickness, and performance as the clearance is varied. The losses increase linearly within the passage and their values increase in direct proportion to tip clearance height. No discernable vortex (discrete) is observed downstream of the rotor.
Document ID
19870058933
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Lakshminarayana, B.
(Pennsylvania State Univ. University Park, PA, United States)
Zhang, J.
(Pennsylvania State Univ. University Park, PA, United States)
Murthy, K. N. S.
(Pennsylvania State University University Park, United States)
Date Acquired
August 13, 2013
Publication Date
January 1, 1987
Subject Category
Aerodynamics
Accession Number
87A46207
Funding Number(s)
CONTRACT_GRANT: NSG-3032
Distribution Limits
Public
Copyright
Other

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