Accession Number : ADA401512


Title :   Alternative Pulse Detonation Engine Ignition System Investigation through Detonation Splitting


Descriptive Note : Master's thesis


Corporate Author : AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING AND MANAGEMENT


Personal Author(s) : Rolling, August J


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/a401512.pdf


Report Date : Mar 2002


Pagination or Media Count : 115


Abstract : A Pulse Detonation Engine (PDE) combusts fuel air mixtures through a form of combustion: detonation. Recent PDE research has focused on designing working subsystems. This investigation continued this trend by examining ignition system alternatives. Existing designs required spark plugs in each separate thrust tube to ignite premixed reactants. A single thrust tube could require the spark plug to fire hundreds of times per second for long durations. The goal was to minimize hardware and increase reliability by limiting the number of ignition sources. This research used a continuously propagating detonation wave as both a thrust mechanism and an ignition system and required only one initial ignition source. This investigation was a proof of concept for such an ignition system. First a systematic look at various geometric effects on detonations was made. These results were used to further examine configurations for splitting detonations, physically dividing one detonation wave into two separate detonation waves. With this knowledge a dual thrust tube system was built and tested proving that a single spark could be used to initiate detonation in separate thrust tubes. Finally, a new tripping device for better deflagration to detonation transition (DDT) was examined. Existing devices induced DDT axially. The new device attempted to reflect an incoming detonation to initiate direct DDT in a cross flow.


Descriptors :   *ROCKET ENGINES , COMBUSTION , THRUST , IGNITION SYSTEMS , DETONATION WAVES , SPARK IGNITION , DEFLAGRATION , DUAL THRUST ROCKET ENGINES , SPARK PLUGS


Subject Categories : Rocket Engines


Distribution Statement : APPROVED FOR PUBLIC RELEASE