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Experimental performance of a 16.10-centimeter-tip-diameter sweptback centrifugal compressor designed for a 6:1 pressure ratioA backswept impeller with design mass flow rate of 1.033 kg/sec was tested with both a vaned diffuser and a vaneless diffuser to establish stage and impeller characteristics. Design stage pressure ratio of 5.9:1 was attained at a flow slightly lower than the design value. Flow range at design speed was 6 percent of choking flow. Impeller axial tip clearance at design speed was varied to determine effect on stage and impeller performance.
Document ID
19770018140
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Klassen, H. A. (NASA Lewis Research Center Cleveland, OH, United States)
Wood, J. R. (NASA Lewis Research Center Cleveland, OH, United States)
Schumann, L. F. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 3, 2013
Publication Date
June 1, 1977
Subject Category
Aerodynamics
Report/Patent Number
E-9074
NASA-TM-X-3552
Accession Number
77N25084
Funding Number(s)
PROJECT: RTOP 505-04
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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