Gas dynamic limits and optimization of pulsed detonation static thrust

Abstract

Pulse detonation engines (PDEs) hold promise to increase the performance of air breathing propulsion systems by taking advantage of the increase in cycle efficiency due to the constant-volume heat addition characteristics of detonative combustion. The performance of a PDE is studied using a onedimensional model originally developed for a combustion wave rotor. The focus is on application to aircraft engine at static and sea level conditions. Detonative combustion of premixed hydrogen and air is ignited by hot gas injection. The design parameters studied are the PDE cycle frequency or cycle time, fuel intake valve timing, and ignition delay timing. The engine performance, measured by thrust per unit area and specific impulse is strongly influenced by the gas wave dynamics.