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RDE Nozzle Computational Design Methodology Development and ApplicationThe rotating detonation engine (RDE) is currently under investigation as an approach to achieving pressure gain combustion for propulsion and power systems. The RDE typically consists of an annulus with one end open (or having a throat and/or nozzle) and the other end valved using non-mechanical, fluidic means. In this study, a total of 6 nozzle design variations were studied for the NPS combustor geometry, using the validated quasi-2D to 3-D coupled simulation approach.
Document ID
20205004925
Document Type
Presentation
Authors
Kenji Miki (Glenn Research Center Cleveland, Ohio, United States)
Daniel E. Paxson (Glenn Research Center Cleveland, Ohio, United States)
Douglas Perkins (Glenn Research Center Cleveland, Ohio, United States)
Shaye Yungster (HX5, LLC)
Date Acquired
July 23, 2020
Subject Category
Aeronautics (General)
Meeting Information
Meeting: AIAA Propulsion and Energy Forum and Exposition Conference
Location: Virtual
Country: US
Start Date: August 24, 2020
End Date: August 26, 2020
Sponsors: GenCorp (United States), Lockheed Martin (United States), Northrop Grumman (United States)
Funding Number(s)
WBS: 469947.04.99.22.0
Distribution Limits
Public
Copyright
Portions of document may include copyright protected material.
Technical Review
Single Expert
Keywords
CFD
Rotating detonation engine
nozzle

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