Performance Studies of Rounded and Annular Pulse Detonation Engine Nozzles

摘要：

Two-dimensional axisymmetric numerical simulation was carried out, using multi-cycle and detailed chemical reaction kinetics of hydrogen/air mixture, to investigate the effect of different nozzles on the rounded and annular pulse detonation engines. For the rounded pulse detonative duct, the largest instantaneous thrust is gained by diverging nozzle; the time-averaged thrust generated by the combined-nozzle with ejector is larger than that by the single-nozzle. The annular pulse detonative duct ejector performance is observed to be stronger than the rounded, which is confirmed from entrainment effect, mixing action, time-averaged mass flow rate of ejection. The process of unsteady ejection can be divided to four stages, and the performance of annular pulse detonation duct ejector is stronger than round pulse detonation duct ejector. Different structure and parameter result in different time-averaged thrust augmentation. By analyzing, the better interior surface, ejector length-to-diameter ratio and axial placement are obtained, which would offer references to augment the performance of pulse detonation engine.

关键词： pulse detonation engine annular nozzle ejection numerical simulation

作者: QIN Ya-xin YU Jun-li GAO Ge

作者单位: National Key Laboratory of Science and Technology on Aero-Engines Beijing University of Aeronautics and Astronautics Beijing, China

会议类型: 国际会议

会议名称: The 3rd International Symposium on Jet Propulsion and Power Engineering(第三届喷气推进与动力工程国际会议 ISJPPE)

会议地点: 南京

会议语种:英文

页码: 190-195

在线出版日期: 2010-09-13（万方平台首次上网日期，不代表论文的发表时间）