A Williams International FJ44-3A turbofan engine was used to demonstrate the high-speed fan noise reduction potential of a foam-metal liner installed in close proximity to the fan rotor. The engine was tested in the NASA Glenn Research Center’s Aeroacoustic Propulsion Laboratory. Two foam-metal liner designs were tested and compared to the hardwall baseline. Traditional single degree-of-freedom liner designs were also evaluated to provide a comparison to the state-of-the art design. This report presents the test setup and documents the test conditions. Far-field acoustic levels and limited engine performance results are also presented. The results show that the foam-metal liner achieved up to 5 dB of attenuation in the forward-quadrant radiated-acoustic power levels, which is equivalent to the traditional single degree-of-freedom liner design. Modest changes in engine performance were noted.
High-Speed Turbofan Noise Reduction Using Foam-Metal Liner Over-the-Rotor
Journal of Aircraft ; 50 , 5 ; 1491-1503
2013-07-24
13 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
High-Speed Turbofan Noise Reduction Using Foam-Metal Liner Over-the-Rotor
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