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Performance of 1380 foot per second tip-speed axial-flow compressor rotor blade tip solidity of 1.5This presents the aerodynamic design parameters along with 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 0.892 and occurred at an equivalent weight flow of 65.0 lb/sec. The total pressure ratio was 1.83 and the total temperature ratio was 1.215. Design efficiency, weight flow, pressure ratio, and temperature ratio were 0.824, 65.3, 1.65, and 1.187, respectively. Stall margin for design speed was 10 percent based on the weight flow and pressure ratio values at peak efficiency and just prior to stall.
Document ID
19720007339
Document Type
Technical Memorandum (TM)
Authors
Ball, C. L.
(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
January 1, 1972
Subject Category
Aerodynamics
Report/Patent Number
NASA-TM-X-2379
E-5723
Funding Number(s)
PROJECT: RTOP 720-03
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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