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Performance of single-stage axial-flow transonic compressor with rotor and stator aspect ratios of 1.63 and 1.78, respectively, and with design pressure ratio of 1.82The overall and blade-element performance of a transonic compressor stage is presented over the stable operating flow range for speeds from 50 to 100 percent of design. The stage was designed for a pressure ratio of 1.82 at a flow 20.2 kg/sec and a tip speed of 455 m/sec. At design speed the stage achieved a peak efficiency of 0.821 at a pressure ratio of 1.817. The stage stall margin at design speed based on conditions at stall and peak efficiency was about 11 percent.
Document ID
19820011348
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
February 1, 1982
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
E-259
NASA-TP-1974
Funding Number(s)
PROJECT: RTOP 505-32-2A
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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