Fan Inlet Disturbances and Their Effect on Static Acoustic Data

[+] Author and Article Information
K. L. Bekofske, R. E. Sheer, J. C. F. Wang

General Electric Co., Corporate Research and Development, Schenectady, N. Y.

J. Eng. Power 99(4), 608-616 (Oct 01, 1977) (9 pages) doi:10.1115/1.3446558 History: Received December 21, 1976; Online July 14, 2010


There is evidence that measurements of fan-rotor inlet noise taken during static test situations are at variance with aircraft engine flight data. In particular, static tests generally yield a significantly higher tone at blade passing frequency than that measured during flight. An experimental program was carried out to investigate this discrepancy. Inlet ground vortices and large-scale inlet turbulence were generated intentionally in an anechoic test chamber. Far-field acoustic measurements and inlet flow field hot film mappings of a fan rotor were then carried out to study the influence of such inlet disturbances at a static test facility. Experimental results indicate that the acoustic effect of such disturbances appears to be less severe for supersonic than for subsonic tip speeds. Further, a reverse flow that occurs on the exterior cowl in static test facilities appears to be an additional prime candidate for creating inlet disturbances and causing variance between flight and static acoustic data.

Copyright © 1977 by ASME
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