Analysis of a Single H2-air Pulse Detonation in a Supersonic Combustor

A two-dimensional unsteady simulation examines the effects of the detonation initiation of an innovative pulsed scramjet system. An analogous supersonic combustor includes a small detonation device with a stoichiometric H 2 -O 2 mixture, meant to augment the fuel penetration, mixing, and early ignition process of a fueled supersonic combustor. The single pulse detonation tube is located right after a single 30 o angled wall flush injection of H 2 into supersonic freestream air, resulting in a Φ s ~1/3. The injection port and detonation tube are followed by a typical 30 o open cavity with L/D=5. The analyses considered herein assume finite-rate conditions with a reduced chemical mechanism for both the hydrogen-oxygen and hydrogen-air mixtures to model the pulse detonation and the scramjet fuel flow. The flow properties in the tube were initialized at atmospheric conditions for the mixture to evolve the pulse, simulated at the head of the tube after detonation has occurred. The results of the small hydrogen detonator delineated a basic evaluation to advance the understanding and configuration design of a supersonic pulse assisted combustor. Nomenclature: