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dc.contributor.advisorBrophy, Christopher M.
dc.contributor.authorNichols, Daniel A.
dc.date.accessioned2012-03-14T17:44:09Z
dc.date.available2012-03-14T17:44:09Z
dc.date.issued2010-12
dc.identifier.urihttp://hdl.handle.net/10945/5093
dc.descriptionApproved for public release; distribution is unlimiteden_US
dc.description.abstractPulse detonation combustion technologies promise the potential of increased thermodynamic efficiency and performance, across a wide range of thrust and power generation applications. Thrust applications would require initial combustor pressures of about 1-4 atm while power applications would require about 4-20 atm. Most of the previous testing of Pulse Detonation Combustors (PDCs) utilized standard atmospheric pressure conditions at sea level, but at elevated temperatures of 300-500°F in the combustor. The current work was motivated by a need to experimentally evaluate the detonation initiation performance of a PDC at elevated combustor pressures. Detonability was evaluated at initial combustor pressures from 2-5 atmospheres and at equivalence ratios of about 0.9-1.1. The experimentation utilized a previously constructed and evaluated three inch diameter combustor that employed swept-ramps as the mechanism for Deflagration-to-Detonation (DDT) initiation. Ramps were removed as the pressure was increased to determine how many sets were necessary to achieve DDT. The legacy PDC was adapted with new and modified components, enabling it to operate at higher pressures and temperatures and for longer durations. It was found that for initial combustor pressures up to 5 atm at least four sets of ramps are required to achieve DDT.en_US
dc.description.urihttp://archive.org/details/sweptrampdetonat109455093
dc.format.extentxvi, 69 p. : ill. (some col.) ;en_US
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. As such, it is in the public domain, and under the provisions of Title 17, United States Code, Section 105, may not be copyrighted.en_US
dc.subject.lcshEngineeringen_US
dc.titleSwept-ramp detonation initiation performance in a high pressure pulse detonation combustoren_US
dc.typeThesisen_US
dc.contributor.secondreaderGannon, Anthony J.
dc.contributor.corporateNaval Postgraduate School (U.S.)
dc.contributor.departmentAstronautical Engineering
dc.description.serviceUS Navy (USN) authoren_US
dc.identifier.oclc697887843
etd.thesisdegree.nameM.S.en_US
etd.thesisdegree.levelMastersen_US
etd.thesisdegree.disciplineAstronautical Engineeringen_US
etd.thesisdegree.grantorNaval Postgraduate Schoolen_US
etd.verifiednoen_US


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