Numerical Analysis on Aerodynamic and Thermal Effects of Plasma Jet in a Mach 2 Combustor

摘要：

　　Supersonic combustion employing an O2 plasma jet(PJ)is investigated numerically.The objective of the present study is to understand the fundamental aspects of aerodynamic and thermal mechanism of ignition and combustion enhancement by a PJ.A fuel(H2)injection and the PJ are injected perpendicularly at sonic speed into the Mach 2 supersonic airflow,and the PJ is located downstream of the fuel injection.Calculation is conducted on a two-dimensional configuration,which is 320mm long and 30mm wide.The Reynolds averaged two-dimensional Navier-Stokes equations,with k-ω SST two-equation turbulent model,are solved in a CFD software ANSYS FLUENT in which a steady density-based implicit solver is adopted.The H2/Air combustion model,including one-step reaction,is used as a kinetic model.Results show that the intense combustion reaction occurs only when the stagnation temperature of the PJ torch is above 500K,which suggests that a specific stagnation temperature of the PJ torch be reached for the ignition of the supersonic combustion.There is little increase in the combustion efficiency when the total temperature of the PJ torch is higher than 500K.Its also found that when the stagnation pressure of the PJ torch is increased,the total equivalence ratio reduces,leading to the decrease of the combustion efficiency.

关键词： Plasma jet Ignition Combustion efficiency Supersonic combustion

作者: Fan Liu Hong Yan

作者单位: Northwestern Polytechnical University,Xian,Shaanxi 710072,China Collaborative Innovation Center for Advanced Aero-Engine,Beijing 100191,China

会议类型: 国际会议

会议名称: The 5th International Symposium on Jet Propulsion and Power Engineering(第五届喷气推进与动力工程国际会议)

会议地点: 北京

会议语种:英文

页码: 1-8

在线出版日期: 2014-09-15（万方平台首次上网日期，不代表论文的发表时间）