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Performance of a single-stage transonic compressor with a blade-tip solidity of 1.5 and comparison with 1.3 and 1.7 solidity stagesThe overall and blade-element performance of a transonic compressor stage with a tip solidity of 1.5 is presented over the stable operating range at rotative speeds from 50 to 100 percent of design speed. State peak efficiency of 0.82 was obtained at a weight flow of 29.4 kg.sec (200.4 (kg/sec)/m2 of annulus area) and a pressure ratio of 1.71. Stall margin at design speed was 14 percent. A comparison of three stages in a solidity study showed that the performance of the 1.5 solidity stage and the 1.3 solidity stage were nearly identical but that the performance of the 1.7 solidity stage was significantly lower.
Document ID
19740002621
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Osborn, W. M. (NASA Lewis Research Center Cleveland, OH, United States)
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 3, 2013
Publication Date
November 1, 1973
Subject Category
Propulsion Systems
Report/Patent Number
E-7255
NASA-TM-X-2926
Accession Number
74N10734
Funding Number(s)
PROJECT: RTOP 501-24
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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