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Attenuation of FJ44 Turbofan Engine Noise with a Foam-Metal Liner Installed Over-the-RotorA Williams International FJ44-3A 3000-lb thrust class turbofan engine was used as a demonstrator for a Foam-Metal Liner (FML) installed in close proximity to the fan. Two FML designs were tested and compared to the hardwall baseline. Traditional single degree-of-freedom liner designs were also evaluated to provide a comparison. Farfield acoustic levels and limited engine performance results are presented in this paper. The results show that the FML achieved up to 5 dB Acoustic Power Level (PWL) overall attenuation in the forward quadrant, equivalent to the traditional liner design. An earlier report presented the test set-up and conditions.
Document ID
20090038701
Acquisition Source
Glenn Research Center
Document Type
Technical Memorandum (TM)
Authors
Sutliff, Daniel L. (NASA Glenn Research Center Cleveland, OH, United States)
Elliott, Dave M. (NASA Glenn Research Center Cleveland, OH, United States)
Jones, Michael G. (NASA Langley Research Center Hampton, VA, United States)
Hartley, Thomas C. (Williams International Walled Lake, MI, United States)
Date Acquired
August 24, 2013
Publication Date
September 1, 2009
Subject Category
Spacecraft Design, Testing And Performance
Report/Patent Number
NASA/TM-2009-215666
AIAA Paper 2009-3141
E-17008
Meeting Information
Meeting: 30th Aeroacoustics Conference
Location: Miami, Fl
Country: United States
Start Date: May 11, 2009
End Date: May 13, 2009
Sponsors: American Inst. of Aeronautics and Astronautics
Funding Number(s)
WBS: WBS 685676.01.03.08.0
Distribution Limits
Public
Copyright
Public Use Permitted.

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