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Effects of casing boundary-layer removal on noise of a turbofan rotorThe effect of casing boundary-layer removal on noise produced by a turbofan rotor was measured. The outlet guide vanes were removed for these tests. A comparison was made between the noise measurements when the boundary layer was bled off and under zero bleed conditions. When the boundary layer was removed, overall sound pressure level was reduced 2 dB with moderate blade loading and 3 dB with heavier blade loading. An analysis of the changes in the spectral density with bleed is presented.
Document ID
19720015344
Acquisition Source
Legacy CDMS
Document Type
Other - NASA Technical Note (TN)
Authors
Goldstein, A. W. (NASA Lewis Research Center Cleveland, OH, United States)
Glaser, F. W. (NASA Lewis Research Center Cleveland, OH, United States)
Coates, J. W. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 2, 2013
Publication Date
April 1, 1972
Subject Category
Aerodynamics
Report/Patent Number
E-6727
NASA-TN-D-6763
Accession Number
72N22994
Funding Number(s)
PROJECT: RTOP 132-80
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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