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dc.contributor.advisorBrophy, Christopher M.
dc.contributor.authorDausen, David F.
dc.date.accessioned2012-03-14T17:35:25Z
dc.date.available2012-03-14T17:35:25Z
dc.date.issued2006-12
dc.identifier.urihttp://hdl.handle.net/10945/2512
dc.description.abstractA premixed gaseous rocket injector was designed and successfully operated over a limited range of fuel-rich operating conditions for the purpose of soot modeling for ethylene and oxygen mixtures. The injector had the advantage of delivering a homogenous mixture to the combustion chamber, lower soot production, and higher performance potential by removing the fuel atomization process which affects the combustion process and is inherent for non-premixed injectors. The premixed injector was operated at oxygen-fuel ratios from 1.0 to 1.8 with a mass flow of 0.024 kg/sec achieving a chamber pressure of 76 psi without propensity of flashback for 0.032[gamma] injector orifices. Increased mass flow rates of 0.027 kg/sec were achieved by increasing the injector orifice diameters to 0.0625[gamma] which produced a chamber pressure of 127 psi and a characteristic exhaust velocity efficiency of 90.1 %. Flashback was eventually observed at an oxygen-to-fuel ratio of 1.2 where the pressure drop was across the injector was less than 388.6 kPa and the bulk mixture velocity through the injector orifices was approximately 90 m/s. Maintaining bulk velocity sufficiently above this value should prevent flashback from occurring, but will likely need to be characterized for additional orifice diameters and pressure differentials.en_US
dc.description.urihttp://archive.org/details/designofpremixed109452512
dc.format.extentxiv, 99 p. : col. ill. ;en_US
dc.publisherMonterey California. Naval Postgraduate Schoolen_US
dc.subject.lcshRocket enginesen_US
dc.subject.lcshEthyleneen_US
dc.subject.lcshOxygenen_US
dc.subject.lcshEngineeringen_US
dc.titleDesign of a premixed gaseous rocket engine injector for ethylene and oxygenen_US
dc.typeThesisen_US
dc.contributor.secondreaderSinibaldi, Jose O.
dc.contributor.corporateNaval Postgraduate School (U.S.).
dc.contributor.departmentMechanical and Astronautical Engineering (MAE)
dc.description.funderFunded by: SEinc307.en_US
dc.identifier.oclc80582142
etd.thesisdegree.nameM.S.en_US
etd.thesisdegree.levelMastersen_US
etd.thesisdegree.disciplineAstronautical Engineeringen_US
etd.thesisdegree.grantorNaval Postgraduate Schoolen_US
etd.verifiednoen_US
dc.description.distributionstatementApproved for public release; distribution is unlimited.


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