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Performance of single-stage axial-flow transonic compressor with rotor and stator aspect ratios of 1.63 and 1.77, respectively, and with design pressure ratio of 2.05The overall and blade-element performance of a transonic compressor stage is presented over the stable operating range for speeds from 50 to 100 percent of design. The stage was designed for a pressure ratio of 2.05 at a flow of 20.2 kg/sec and a tip speed of 455 m/sec. At design speed the rotor and stage achieved peak efficiencies of 0.849 and 0.831, respectively, at the minimum flow condition. The stage stall point occurred at a flow higher than the design flow.
Document ID
19820014395
Document Type
Technical Publication (TP)
Authors
Moore, R. D.
(NASA Lewis Research Center Cleveland, OH, United States)
Reid, L.
(NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 4, 2013
Publication Date
April 1, 1982
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
NAS 1.60:2001
NASA-TP-2001
E-334
Funding Number(s)
PROJECT: RTOP 505-32-2A
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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