NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Back to Results
An experimental study of the compressor rotor blade boundary layerThe three-dimensional turbulent boundary layer developing on a rotor blade of an axial flow compressor was measured using a miniature 'x' configuration hot-wire probe. The measurements were carried out at nine radial locations on both surfaces of the blade at various chordwise locations. The data derived includes streamwise and radial mean velocities and turbulence intensities. The validity of conventional velocity profiles such as the 'power law profile' for the streamwise profile, and Mager and Eichelbrenner's for the radial profile, is examined. A modification to Mager's crossflow profile is proposed. Away from the blade tip, the streamwise component of the blade boundary layer seems to be mainly influenced by the streamwise pressure gradient. Near the tip of the blade, the behavior of the blade boundary layer is affected by the tip leakage flow and the annulus wall boundary layer. The 'tangential blockage' due to the blade boundary layer is derived from the data. The profile losses are found to be less than that of an equivalent cascade, except in the tip region of the blade.
Document ID
19840064204
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Pouagare, M.
(Pennsylvania State Univ. University Park, PA, United States)
Lakshminarayana, B.
(Pennsylvania State University University Park, PA, United States)
Galmes, J. M.
(Pennsylvania State University University Park, PA; SocieteEuropeenne de Propulsion, Vernon, Eure, France)
Date Acquired
August 12, 2013
Publication Date
June 1, 1984
Subject Category
Aerodynamics
Report/Patent Number
ASME PAPER 84-GT-193
Accession Number
84A46991
Funding Number(s)
CONTRACT_GRANT: NSG-3266
Distribution Limits
Public
Copyright
Other

Available Downloads

There are no available downloads for this record.
No Preview Available