Gasdynamic inlet isolation in rotating detonation engine

dc.contributor.advisorSinibaldi, Jose O.
dc.contributor.advisorBrophy, Christopher M.
dc.contributor.authorLim, Wei Han Eugene.
dc.contributor.corporateNaval Postgraduate School (U.S.)
dc.contributor.departmentMechanical Engineering
dc.date.accessioned2012-03-14T17:44:04Z
dc.date.available2012-03-14T17:44:04Z
dc.date.issued2010-12
dc.descriptionIncludes supplementary materialen_US
dc.description.abstractThe Rotating Detonation Engine (RDE) concept represents the next-generation of detonation-based engines as it provides higher performance and near constant thrust with a simpler overall design. Since RDE systems are in the early stage of development, the physics of engine design is yet to be fully understood and developed. A critical concern of these systems is the practical isolation of the reactant injection manifold and supply system from the combustor pressure oscillations. For this study, the gasdynamic conditions that existed at the combustor inlet are investigated and characterized. Using a shocktube test case for a Hydrogen-Air mixture, various numerical schemes, number of chemical reactions, mesh topology and mesh refinement are first investigated to reliable reproduce the Chapman-Jouguet conditions. It was found that explicit 4th Order Rungekutta scheme using structured mesh topology, 18 species and 9 reactions with a maximum mesh cell size of 0.05 mm was required to reproduce the Chapman-Jouguet conditions. Once the suitable parameters were identified, a full 2D RDE simulation was carried out to characterize the gasdynamic inlet conditions.en_US
dc.description.distributionstatementApproved for public release; distribution is unlimited.
dc.description.funderN001410WX20832.en_US
dc.description.serviceSingapore Armed Forces authoren_US
dc.description.urihttp://archive.org/details/gasdynamicinleti109455068
dc.format.extentxvi, 103 p. : ill. ;en_US
dc.identifier.oclc698376057
dc.identifier.urihttps://hdl.handle.net/10945/5068
dc.publisherMonterey, California. Naval Postgraduate Schoolen_US
dc.rightsThis publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States.en_US
dc.subject.lcshMechanical engineeringen_US
dc.subject.lcshSignal processingen_US
dc.titleGasdynamic inlet isolation in rotating detonation engineen_US
dc.typeThesisen_US
dspace.entity.typePublication
etd.thesisdegree.disciplineMechanical Engineeringen_US
etd.thesisdegree.grantorNaval Postgraduate Schoolen_US
etd.thesisdegree.levelMastersen_US
etd.thesisdegree.nameM.S.en_US
etd.verifiednoen_US
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