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axial flow rotor unsteady response to circumferential inflow distortionsThe unsteady response of an axial flow fan rotor to steady, circumferential inflow velocity and stagnation pressure distortions is assessed by two different methods. These are: (1) investigation of the unsteady normal force and pitching moment on a chordwise element of a rotor blade; and (2) investigation of the variation of the stagnation pressure distortion between the inlet and exit of the rotor. Experimental measurements of these unsteady characteristics are presented as a function of the geometry of the rotor -- stagger angle, solidity and steady angle of incidence -- for sinusoidally varying circumferential distortions with different numbers of distortion cycles. These measurements are compared with several theoretical analyses. While these comparisons indicate some of the deficiencies which exist in the theories, the existence of an unsteady cascade effect and the ability of the theories to adequately predict the trend of the unsteady response due to variations in reduced frequency, rotor stagger angle, solidity and mean incidence angle is clearly demonstrated.
Document ID
19760018098
Document Type
Conference Paper
Authors
Bruce, E. P.
(Pennsylvania State Univ. University Park, PA, 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
Funding Number(s)
PROJECT: NR PROJ. 098-038
OTHER: NSG-3031
PROJECT: PROJ. SQUID
OTHER: N00014-67-A-0226-0005
Distribution Limits
Public
Copyright
Other

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