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Performance of a 1.20 pressure ratio STOL fan stage at three rotor blade setting anglesA model of a short takeoff and landing (STOL) fan stage was testedin a single-stage compressor research facility. Surveys of the airflow 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 meters per second and a weight flow of 31.2 kilograms per second, the stage pressure ratio of 1.15 was less than the design value of 1.2. The stage was tested with the rotor blades reset for more flow. Design pressure ratio was achieved and surpassed with the minus 5 deg and minus 7 deg resets, respectively. The stage efficiency was 0.88 for the minus 5 deg reset and 0.85 for the minus 7 deg reset.
Document ID
19730018974
Document Type
Technical Memorandum (TM)
Authors
Lewis, G. W., Jr.
(NASA Lewis Research Center Cleveland, OH, United States)
Moore, R. D.
(NASA Lewis Research Center Cleveland, OH, United States)
Kovich, G.
(NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 2, 2013
Publication Date
July 1, 1973
Subject Category
Propulsion Systems
Report/Patent Number
NASA-TM-X-2837
E-7434
Funding Number(s)
PROJECT: RTOP 501-24
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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