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Overall and blade-element performance of a 1.20-pressure-ratio fan stage at design blade setting angleA 51-cm-diam. model of a short-haul fan stage was tested. Surveys of the air flow conditions ahead of the rotor, between the rotor and stator, and behind the stator were made over the stable operating range of the stage. At the design speed of 213.3 m/sec and weight flow of 26.7 kg/sec, the stage pressure ratio and efficiency are 1.18 and 0.87, respectively. The rotor peak efficiency of 0.92 occurred at flow rate of 30.5 kg/sec. Peak stage efficiency of 0.09 was obtained at 110 percent speed at a pressure ratio of 1.218 and a weight flow of 30.2 kg/sec. Maximum stage pressure ratio is 1.269 at 120 percent speed.
Document ID
19740025117
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Lewis, G. W., Jr. (NASA Lewis Research Center Cleveland, OH, United States)
Tysl, E. R. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 3, 2013
Publication Date
September 1, 1974
Subject Category
Propulsion Systems
Report/Patent Number
E-7791
NASA-TM-X-3101
Accession Number
74N33230
Funding Number(s)
PROJECT: RTOP 501-24
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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