NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Back to Results
Performance of 1380-foot-per-second tip-speed axial-flow compressor rotor with blade tip solidity of 1.1The aerodynamic design parameters are presented 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 0.853 and occured at an equivalent weight flow of 65.7lb/sec. The total pressure ratio was 1.68. Design efficiency, weight flow, pressure ratio, and temperature ratio were 0.822, 65.3, 1.65, and 1.187, respectively. Stall margin for design speed was 14 percent based on the weight flows and pressure ratios at peak efficiency and just prior to stall.
Document ID
19720011348
Document Type
Technical Memorandum (TM)
Authors
Janetzke, D. C.
(NASA Lewis Research Center Cleveland, OH, United States)
Ball, C. L.
(NASA Lewis Research Center Cleveland, OH, United States)
Hager, R. D.
(NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 2, 2013
Publication Date
March 1, 1972
Subject Category
Aerodynamics
Report/Patent Number
NASA-TM-X-2449
E-6686
Funding Number(s)
PROJECT: RTOP 764-74
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

Available Downloads

NameType 19720011348.pdf STI
No Preview Available