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Performance of a 1380-foot-per-second-tip-speed axial-flow compressor rotor with a blade tip solidity of 1.3Aerodynamic design parameters are presented along the overall and blade element performance, of an axial flow compressor rotor designed to study the effects of blade solidity on efficiency and stall margin. At design speed the peak efficiency was 0.844 and occurred at an equivalent weight flow of 63.5 lb/sec with a total pressure ratio of 1.801. Design efficiency, pressure ratio, and weight flow 0.814, 1.65, and 65.3(41.1 lb/sec/sq ft of annulus area), respectively. Stall margin for design speed was 6.4 percent based on the weight flow and pressure ratio values at peak efficiency and just prior to stall.
Document ID
19720012341
Document Type
Technical Memorandum (TM)
Authors
Hager, R. D.
(NASA Lewis Research Center Cleveland, OH, United States)
Janetzke, D. C.
(NASA Lewis Research Center Cleveland, OH, United States)
Reid, L.
(NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 2, 2013
Publication Date
April 1, 1972
Subject Category
Aerodynamics
Report/Patent Number
NASA-TM-X-2448
E-6503
Accession Number
72N19991
Funding Number(s)
PROJECT: RTOP 764-74
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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