Design of a Coaxial Split Flow Pulse Detonation Engine
Abstract
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.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jun 01, 2006
- Accession Number
- ADA451403
Entities
People
- Philip D. Hall
Organizations
- Naval Postgraduate School