【作者】 张家奇； 李清廉； 李晓晖； 于杨； 于欣；

【Author】 Zhang Jiaqi;Li Qinglian;Li Xiaohui;Yu Yang;Yu Xin;College of Aerospace and Engineering,National University of Defense Technology;Science and Technology on Scramjet Laboratory,National University of Defense Technology;National key Laboratory of Science and technology on Tunable Laser,Harbin Institute of Technology;Institue of Opto-electronics,Harbin Institute of Technology;

【机构】 国防科学技术大学航天科学与工程学院； 国防科学技术大学高超声速冲压发动机技术重点实验室； 哈尔滨工业大学可调谐激光技术重点实验室； 哈尔滨工业大学光电子技术研究所；

【摘要】 设计了富燃区域点火的小推力气氧气甲烷样机,针对该样机开展了激光点火试验,旨在验证富燃区域点火的可行性、研究它在各工况下的点火位置边界与点火延迟等特性。结果表明点火区余氧系数0.267时,在头腔方向无点火位置边界;在点火的位置原点,点火区余氧系数边界为0.231~0.255,起火后熄火原因是点火区域附近没有合适的燃烧混合比。各次试验均为第一个火花点燃、T90均在20ms左右。更多还原

【Abstract】 A small thrust GO₂/GCH₄ engine with fuel-rich ignition area was designed for laser igntion. Experimental studies were performed to investigate the igntion characteristics of the engine in various condistions, including igntion boundary and ignition delay. Conclusion shows that there is no ignition boundary in head end for EOI 0.267. At origin point, EIO boundary varies from 0.231-0.255, where the ignited mixture extinguishes during the combustion developing. This is because there is no proper mix ratio nearby igntion area. Experiments show that igntion was realized by the first spark which gives a 20 ms T90 in every successive case.更多还原