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Numerical Investigation of a Shielded Chevron NozzleReynolds-Averaged Navier-Stokes simulations have been performed on a three-stream inverted velocity profile nozzle with and without various configurations of chevrons attached. The nozzle was mounted on a planform to imitate an engine mounted above a wing, shielding ground observers from engine noise. Several chevron designs intended to aggressively mix the jet and move noise sources upstream for shielding were examined to investigate there effects on noise and thrust. Numerical results for the baseline nozzle and one chevron configuration were compared with far-field noise and particle image velocimetry data obtained in NASA Glenn Research Center's Aero-Acoustic Propulsion Laboratory. A configuration in which chevrons alternate penetration into the primary stream and tertiary fan stream was explored using the Modern Design of Experiments approach. Short, high-penetration chevrons demonstrated a significant noise reduction for a relatively small thrust penalty.
Document ID
20190004929
Acquisition Source
Glenn Research Center
Document Type
Contractor Report (CR)
Authors
Heberling, Brian C. (Vantage Partners, LLC Brook Park, OH, United States)
Date Acquired
May 2, 2019
Publication Date
March 1, 2019
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
E-19656
NASA/CR-2019-220066
Funding Number(s)
CONTRACT_GRANT: NNC12BA01B
WBS: 109492.02.03.01.01
Distribution Limits
Public
Copyright
Public Use Permitted.
Technical Review
Single Expert
Keywords
shielding
chevrons
jet noise

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