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Performance of a tandem-rotor/tandem-stator conical-flow compressor designed for a pressure ratio of 3A conical-flow compressor stage with a large radius change through the rotor was tested at three values of rotor tip clearance. The stage had a tandem rotor and a tandem stator. Peak efficiency at design speed was 0.774 at a pressure ratio of 2.613. The rotor was tested without the stator, and detailed survey data were obtained for each rotor blade row. Overall peak rotor efficiency was 0.871 at a pressure ratio of 2.952.
Document ID
19830002788
Acquisition Source
Legacy CDMS
Document Type
Technical Publication (TP)
Authors
Wood, J. R. (NASA Lewis Research Center Cleveland, OH, United States)
Owen, A. K. (Army Aviation Research and Development Command Cleveland, Ohio, United States)
Schumann, L. F. (Army Aviation Research and Development Command Cleveland, Ohio, United States)
Date Acquired
September 4, 2013
Publication Date
October 1, 1982
Subject Category
Aerodynamics
Report/Patent Number
NAS 1.60:2034
E-369
NASA-TP-2034
AVRADCOM-TR-81-C-5
Report Number: NAS 1.60:2034
Report Number: E-369
Report Number: NASA-TP-2034
Report Number: AVRADCOM-TR-81-C-5
Accession Number
83N11058
Funding Number(s)
PROJECT: RTOP 505-32-2A
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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