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Acoustic Directivity and Insertion Loss Measurements of Advanced Liners Installed the Inlet of the DGEN Aeropropulsion Research TurbofanThe NASA Glenn Research Center’s DGEN Aeropropulsion Research Turbofan (DART) is based on the Price Induction DGEN380—a small, ~500-lbf thrust class, high-bypass, geared-turbofan engine with a separate flow nozzle. The general characteristics of the DART make it an ideal candidate for utilization as a test bed for engine aeroacoustic research in a relevant performance environment. The DART was used to document the efficacy of acoustic liners installed in the inlet of the DGEN380. An advanced multi-degree-of-freedom liner (MDOF) was designed and tested, along with a traditional single-degree-of- freedom liner (SDOF), and those results compared to a hard-wall baseline inlet. Farfield acoustic data were acquired from an external array, evaluated, and reported here-in terms of overall, broadband, and tonal components of the insertion loss.
Document ID
20190011719
Acquisition Source
Glenn Research Center
Document Type
Technical Memorandum (TM)
Authors
Sutliff, Daniel L. (NASA Glenn Research Center Cleveland, OH, United States)
Jones, Michael G. (NASA Langley Research Center Hampton, VA, United States)
Nark, Douglas M. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
May 8, 2019
Publication Date
May 1, 2019
Subject Category
Acoustics
Report/Patent Number
E-19677
NASA/TM-2019-220161
Funding Number(s)
WBS: 081876.02.03.50.03.06
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Technical Review
Single Expert
Keywords
Noise Reduction
Acoustics
Aeroacoustics

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