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Performance of a single-stage transonic compressor with a blade-tip solidity of 1.3The design and experimental performance of a 50-centimeter-diameter, single stage, axial flow, transonic compressor with a blade tip solidity of 1.3 are presented. Radial surveys were made of the flow conditions for both the rotor and stator. At design speed, peak efficiencies for both rotor and stage were 0.87 and 0.82, respectively, and occurred at an equivalent weight flow of 29.6 kilograms per second (202 kg/sec/sq m of annulus area). At peak efficiency, the total pressure ratios for both rotor and stage were 1.79 and 1.73, respectively. Stall margin for the stage was 17 percent.
Document ID
19730002275
Document Type
Technical Memorandum (TM)
Authors
Urasek, D. C.
(NASA Lewis Research Center Cleveland, OH, United States)
Moore, R. D.
(NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 2, 2013
Publication Date
November 1, 1972
Subject Category
Aerodynamics
Report/Patent Number
E-6763
NASA-TM-X-2645
Funding Number(s)
PROJECT: RTOP 501-24
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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