Abstract
Hydrogen combustion assisted by the oxygen plasma jet (PJ) in a Mach 1.9 supersonic internal flow was numerically investigated. Mixing and combustion behavior were compared between upstream and downstream fuel injections. For hydrogen injection downstream of the PJ, only weak combustion occurred even with a relatively high electric power input because of the rapid decrease in the ignitability of the PJ plume in the downstream. In contrast, intensive combustion easily occurred for hydrogen injection upstream of the PJ, with a relatively low electric power input, and a pseudo shock wave (PSW) was formed upstream of the fuel injector. The position of the PSW strongly affected the fuel mixing with the main airflow. The mixing and combustion of the fuel were rapidly enhanced by the formation of the leading shock wave of the PSW upstream of the fuel injector. Counter-rotating vortex pairs behind the fuel jet and PJ were enlarged by the PSW formation. The enlarged vortex structure behind the PJ was the main cause of the combustion enhancement.
Sign-in/Register to access full text options 
Free) 
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a call
