Future Navy Capabilities indicate the need for a supersonic cruise missile. Thus the need exists for a low cost, light-weight, and efficient means of supersonic propulsion. NPS has been developing the Pulse Detonation Engine, which in theory has a thermodynamic efficiency greater than 50% as compared to 35% for state of the art constant-pressure cycles currently in use in gas turbines/ramjets/scramjets. Nonetheless, there are two major problems in the development of this engine. These are the increase of the propulsive efficiency by removing the oxygen-assisted initiator currently in use, and the reduction of internal total pressure losses caused by the highly constrictive internal flow-path geometry currently required to promote the deflagration to detonation transition (DDT). The aforementioned problems have been addressed and a viable design proposed through the implementation of a novel Transient Plasma Ignition system and a split-flow path engine geometry as described in this work. Future work will concentrate on the development of a performance measurement test rig to experimentally assess the designs presented herein. / US Navy (USN) author.
| Identifer | oai:union.ndltd.org:nps.edu/oai:calhoun.nps.edu:10945/2778 |
| Date | 06 1900 |
| Creators | Hall, Philip D. |
| Contributors | Sinibaldi, Jose O., Brophy, Christopher M., Naval Postgraduate School (U.S.), Mechanical Engineering |
| Publisher | Monterey, California. Naval Postgraduate School |
| Source Sets | Naval Postgraduate School |
| Detected Language | English |
| Type | Thesis |
| Format | xiv, 43 p. : ill. (some col.) ;, application/pdf |
| Rights | Approved for public release, distribution unlimited |
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