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Experimental and computational results from a large low-speed centrifugal impellerAn experimental and computational investigation of the NASA Low-Speed Centrifugal Compressor (LSCC) flow field has been conducted using laser anemometry and Dawes' 3D viscous code. The experimental configuration consists of a backswept impeller followed by a vaneless diffuser. Measurements of the three-dimensional velocity field were acquired at several measurement planes through the compressor. The measurements describe both the throughflow and secondary velocity field along each measurement plane and in several cases provide details of the flow within the blade boundary layers. The experimental and computational results provide a clear understanding of the development of the throughflow momentum wake which is characteristic of centrifugal compressors.
Document ID
19940015663
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Hathaway, M. D. (Army Research Lab. Cleveland, OH., United States)
Chriss, R. M. (NASA Lewis Research Center Cleveland, OH, United States)
Wood, J. R. (NASA Lewis Research Center Cleveland, OH, United States)
Strazisar, A. J. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 6, 2013
Publication Date
December 1, 1993
Subject Category
Aerodynamics
Report/Patent Number
E-8258
NASA-TM-106421
NAS 1.15:106421
ARL-TR-331
Meeting Information
Meeting: eeting of the AGARD Propulsion and Energetics Panel, Technology Requirements for Small Gas Turbine Engines
Location: Montreal, Ontario
Country: Canada
Start Date: October 4, 1993
End Date: October 6, 1993
Sponsors: Advisory Group for Aerospace Research and Development
Accession Number
94N20136
Funding Number(s)
PROJECT: DA PROJ. 1L1-61102-AH-45
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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