Fin-Guided Fuel Injection Enhancements for Low Aspect Ratio Scramjet Combustors

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dc.contributor.advisorYu, Kenneth Hen_US
dc.contributor.authorBalar, Rama Ashoken_US
dc.contributor.departmentAerospace Engineeringen_US
dc.contributor.publisherDigital Repository at the University of Marylanden_US
dc.contributor.publisherUniversity of Maryland (College Park, Md.)en_US
dc.date.accessioned2007-06-22T05:37:51Z
dc.date.available2007-06-22T05:37:51Z
dc.date.issued2007-05-08
dc.description.abstractCharacterization of a three-dimensional Mach 2 scramjet combustor with aspect ratio one has been conducted in order to provide baseline performance data. The maximum combustion performance was achieved at an equivalence ratio of 0.25 due to poor mixing. Subsequent fuel injection studies investigated transverse and ramped parallel mixing schemes in a Mach 2 duct. It was shown ramped injection required too high of flow blockage to be practical for efficient mixing. From these studies a new Fin-Guided fuel injection technique was established. Substantial improvement in mixing performance was observed through pressure traces, Schlieren and Mie-scattering. With the use of Fin-Guided Injection the fuel penetration height was increased by 100~120% and the flow losses associated with jet-induced shocks were reduced by 13~30% over injection without a fin. The results open up the possibility of further increasing performance by optimizing the fin height and the fuel injection angle behind the fin.en_US
dc.format.extent7551358 bytes
dc.format.mimetypeapplication/pdf
dc.identifier.urihttp://hdl.handle.net/1903/6939
dc.language.isoen_US
dc.subject.pqcontrolledEngineering, Aerospaceen_US
dc.subject.pqcontrolledEngineering, Aerospaceen_US
dc.subject.pquncontrolledFuel Injectionen_US
dc.subject.pquncontrolledSupersonic fuel injectionen_US
dc.subject.pquncontrolledFin-guideden_US
dc.subject.pquncontrolledLow aspect ratio combustoren_US
dc.subject.pquncontrolledMixing enhancementen_US
dc.titleFin-Guided Fuel Injection Enhancements for Low Aspect Ratio Scramjet Combustorsen_US
dc.typeThesisen_US

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