Design, Modeling and Performance of a Split Path JP-10/Air Pulse Detonation Engine
Abstract
The initiation of a detonation in Pulse Detonation Engines (PDE) has been identified as one of the critical and enabling technologies for PDEs. In particular, the initiation of practical fuel-air mixtures containing liquid droplets without supplementary oxygen or other high loss mechanisms is a capability that could enable the PDE to exceed the performance of ramjets and expendable turbo-machinery based systems. Although past engine designs have relied upon a sensitive fuel/oxygen initiator unit or unrealistic gaseous fuels such as ethylene and propane, a PDE was designed and partially tested that has eliminated the requirement for supplementary oxygen as well as enabling the use of a JP-10, high-density liquid fuel. Air flow through segments of this PDE was simulated using Computational Fluid Dynamics and experimentally evaluated in the laboratory at simulated flight conditions, including supersonic cruising conditions. The spiral lined initiator demonstrated a lower total pressure loss when compared to the geometry with rings, and thus was the preferred initiator configuration. Experimental values for the turbulence were found to be significantly lower than the computed values at similar conditions. Finally, successful ignitions of the JP-10/Air initiator at frequencies of up to 20 Hz were experimentally demonstrated.
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 01, 2006
- Accession Number
- ADA462628
Entities
People
- Patrick D. Hutcheson
Organizations
- Naval Postgraduate School