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dc.contributor.advisorBrophy, Christopher M.
dc.contributor.authorWerner, Steven P.
dc.date.accessioned2012-03-14T17:37:32Z
dc.date.available2012-03-14T17:37:32Z
dc.date.issued2002-12
dc.identifier.urihttp://hdl.handle.net/10945/3183
dc.descriptionApproved for public release; distribution in unlimited.en_US
dc.description.abstractOperational characteristics of a valveless pulse detonation engine system are being characterized by both experimental and computational efforts. The detonation diffraction process from a small "initiator" combustor to a larger diameter main combustor in a continuous airflow configuration was evaluated during multi-cycle operation of a pulse detonation engine. The multi-cycle detonation experiments were performed on an axisymetric engine geometry operating on both ethylene and propane fuel/air mixtures. The new design explored the effect of forward relief area on performance and its ability to isolate the detonation products from the incoming air flow during cyclic operation. The use of a small fuel-oxygen initiator to initiate a fuel/air detonation in a larger main combustor has been achieved and has demonstrated the benefit of generating an overdriven detonation condition near the diffraction plane for enhanced transmission to a larger combustor. Mach reflections have been observed on the outer wall downstream of the diffraction plane for the two-dimensional geometry and appear to be the primary re-initiation mechanisms for the re-established fuel-air detonations for this geometry. Multi-cycle tests have successfully evaluated initiator/main combustor diameter ratios of up to 1.58 and are expected to continue through 2.0.en_US
dc.description.urihttp://archive.org/details/initiatordiffrac109453183
dc.format.extentxii, 49 p. : col. ill. ;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. Copyright protection is not available for this work in the United States.en_US
dc.subject.lcshSpace vehiclesen_US
dc.subject.lcshPropulsion systemsen_US
dc.titleInitiator diffraction limits for pulse detonation engine operationen_US
dc.typeThesisen_US
dc.contributor.secondreaderSinibaldi, Jose O.
dc.contributor.departmentAeronautics and Astronautics
dc.subject.authorPulse Detonation Engineen_US
dc.subject.authorDetonationen_US
dc.subject.authorValvelessen_US
dc.subject.authorSpace Propulsionen_US
dc.subject.authorHydrocarbon Fuelsen_US
dc.description.funderFUNDED BY: N00014-02-2-0153.en_US
dc.description.serviceLieutenant, United States Navyen_US
etd.thesisdegree.nameM.S. in Astronautical Engineeringen_US
etd.thesisdegree.levelMastersen_US
etd.thesisdegree.disciplineAstronautical Engineeringen_US
etd.thesisdegree.grantorNaval Postgraduate Schoolen_US


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