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Performance of two-stage fan having low-aspect-ratio first-stage rotor bladingThe NASA two stage fan was tested with a low aspect ratio first stage rotor having no midspan dampers. At design speed the fan achieved an adiabatic design efficiency of 0.846, and peak efficiencies for the first stage and rotor of 0.870 and 0.906, respectively. Peak efficiency occurred very close to the stall line. In an attempt to improve stall margin, the fan was retested with circumferentially grooved casing treatment and with a series of stator blade resets. Results showed no improvement in stall margin with casing treatment but increased to 8 percent with stator blade reset.
Document ID
19790018972
Document Type
Technical Publication (TP)
Authors
Urasek, D. C. (NASA Lewis Research Center Cleveland, OH, United States)
Gorrell, W. T. (Army Aviation Res. and Develop. Command Cleveland, United States)
Cunnan, W. S. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 3, 2013
Publication Date
August 1, 1979
Subject Category
AIRCRAFT PROPULSION AND POWER
Report/Patent Number
E-9237
AVRADCOM-TR-78-49
NASA-TP-1493
Funding Number(s)
PROJECT: RTOP 505-04
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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