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the effect of circumferential distortion on fan performance at two levels of blade loadingSingle stage fans designed for two levels of pressure ratio or blade loading were subjected to screen induced circumferential distortions of 90 degree extent. Both fan rotors were designed for a blade tip speed of 425 m/sec, blade solidity of 1.3 and a hub-to-tip radius ratio of 0.5. Circumferential measurements of total pressure, temperature, static pressure, and flow angle were obtained at the hub, mean and tip radii at five axial stations. Rotor loading level did not appear to have a significant influence on rotor response to distorted flow. Losses in overall pressure ratio due to distortion were most severe in the stator hub region of the more highly loaded stage. At the near stall operating condition tip and hub regions of (either) rotor demonstrated different response characteristics to the distorted flow. No effect of loading was apparent on interactions between rotor and upstream distorted flow fields.
Document ID
19760018096
Document Type
Conference Paper
Authors
Hartmann, M. J.
(NASA Lewis Research Center Cleveland, OH, United States)
Sanger, N. L.
(NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
August 8, 2013
Publication Date
April 1, 1976
Publication Information
Publication: AGARD Unsteady Phenomena in Turbomachinery
Subject Category
AIRCRAFT PROPULSION AND POWER
Distribution Limits
Public
Copyright
Other

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