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dc.contributor.advisorFarokhi, Saeed
dc.contributor.authorHwang, Seung-Jae
dc.date.accessioned2011-09-22T04:11:46Z
dc.date.available2011-09-22T04:11:46Z
dc.date.issued2011-06-09
dc.date.submitted2011
dc.identifier.otherhttp://dissertations.umi.com/ku:11613
dc.identifier.urihttp://hdl.handle.net/1808/8080
dc.description.abstractNumerical simulations of the scramjet combustor by using the commercial CFD code Fluent with the coupled implicit method with second-order accurate discretization have been obtained for the reacting flows with the parallel fuel injection (ramp injection) and normal fuel injection (wall injection) schemes. Incorporated in the scramjet combustors are delta tabs and suction collars of two types as means of mixing enhancement. The main mechanism of the tabs and suction collars for mixing enhancement is the generation of streamwise vorticity and providing outstanding flameholding capability along with the induced global instability of the shear layer. The idea has been previously recommended for mixing enhancement of the scramjet combustor, but no experimental or computational data on the combustor performance has been reported, yet. The finite rate reaction model is used for the species transport model that only considers four species, H2, O2, H2O and N2. Vitiated air (mass fraction of O2, H2O, and N2 being 0.198, 0.139, and 0.663, respectively) enters the combustor at Mach number of 2.5 at a stagnation temperature and pressure of 1500 K and 101,325 Pa, respectively. The equivalence ratio is fixed at 0.45 in the present study. An optimization study of the combinations of the tabs and suction collars has been performed. Uninstalled thrust force for the optimal combination which was composed of the relieved ramp, 4 delta tabs, suction collar type I and 4 delta tabs in the fuel inlet scheme produced an additional 73% increase in thrust with only an additional 3.37% loss of the total pressure compared to the ramp injection alone, i.e., the baseline case. The numerical results clearly indicate that the fuel injection schemes investigated in the present study are more efficient than a strut or multi-staged strut and wall injection scheme.
dc.format.extent104 pages
dc.language.isoen
dc.publisherUniversity of Kansas
dc.rightsThis item is protected by copyright and unless otherwise specified the copyright of this thesis/dissertation is held by the author.
dc.subjectAerospace engineering
dc.subjectCombustor
dc.subjectEnhanced
dc.subjectMixing
dc.subjectScramjet
dc.subjectSuction collar
dc.subjectTabs
dc.titleNumerical Simulation of Enhanced Mixing in Scramjet Combustor Using Ramp, Tabs and Suction Collar
dc.typeDissertation
dc.contributor.cmtememberTaghavi, Ray
dc.contributor.cmtememberBarrett-Gonzalez, Ron
dc.contributor.cmtememberKeshmiri, Shahriar
dc.contributor.cmtememberHuang, Weizhang
dc.thesis.degreeDisciplineAerospace Engineering
dc.thesis.degreeLevelPh.D.
kusw.oastatusna
kusw.oapolicyThis item does not meet KU Open Access policy criteria.
kusw.bibid7643013
dc.rights.accessrightsopenAccess


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