冲压发动机燃烧室点火性能试验  

Experiments on ignition performance of ramjet combustor

作　　者：李春光[1,2] 吉洪湖[1] 王健[2] 张振家 

机构地区：[1]南京航空航天大学能源与动力学院,江苏南京210016 [2]中国航天科工集团三十一研究所高超声速冲压发动机技术重点实验室,北京100074

出　　处：《推进技术》2011年第4期530-533,共4页Journal of Propulsion Technology

摘　　要：对具有四个旁侧进气道带机械火焰稳定装置的整体式冲压喷气发动机的起动点火性能进行了试验研究,分析了点火能量、稳定器槽宽、来流温度、点火余气系数等因素对冲压燃烧室的点火延迟时间的影响。研究表明,点火能量是影响冲压燃烧室点火起动的重要因素,通过提高点火能量可以实现冲压发动机的快速点火起动;另外,稳定系数越高,点火余气系数对应的燃烧效率越高,发动机点火越容易。The experimental investigations on the ignition performance of an integrated ramjet engine with 4-side inlets were performed as well as a flame stabilization device.The influence of the ignition energy supplied,the gut width of the stabilizer,the coming flow temperature and the equivalence ratio on the ignition response time for the ramjet were studied.The results indicated that the ignition energy is an important factor for the ignition and starting of the ramjet combustor.The increase of the ignition energy supplied is able to rapidly start the ramjet engine.In addition,the higher the flame stabilization coefficients is,the higher combustion efficiency corresponding to the equivalence ratio at the ignition and the easier the ramjet ignition.

关 键 词：冲压喷气发动机 燃烧室 火焰稳定器 点火试验 点火延迟 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]