中心分级燃烧室点火性能试验研究  

Experimental Investigation on Ignition Performance of Internally-Staged Combustor

作　　者：王延胜[1] 林宇震[1] 李林[1] 薛鑫[1] 

机构地区：[1]北京航空航天大学能源与动力工程学院,航空发动机气动热力国家级重点实验室,北京100191

出　　处：《推进技术》2016年第1期98-104,共7页Journal of Propulsion Technology

摘　　要：对中心分级燃烧室常温常压和常温低压下的点火性能进行了试验研究。在进口压力分别为0.1,0.035,0.03MPa,进口温度为常温的条件下,试验研究了不同空气压降（0.5%~6%）下的贫油点火油气比,获得了其点火边界曲线。试验结果表明：随着压力降增加,在各种燃烧室进口压力下的贫油点火油气比具有一个最低值;随着进口压力减小,这个最低值所对应的压降不断降低,同时贫油点火油气比升高。通过分析进口空气条件、燃烧室参考速度和燃油SMD对点火性能的影响,得到了其点火模型。At ambient temperature and pressure,ambient temperature and low pressure,the ignition performance of the internally-staged combustor was experimentally investigated. The inlet air pressure were 0.1,0.035,and 0.03 MPa,respectively,and inlet air temperature was room temperature,ignition boundary was obtained at a series of air pressure drops（0.5%~6%）. The experimental results indicate that,with the increase of pressure drop,the fuel-air-ratio（FAR） of lean ignition has a minimum value at different inlet air pressure. With the decrease of inlet air pressure,the pressure drop corresponding to the minimum FAR was decreasing,and FAR of lean ignition increases. A model of lean ignition was obtained by analyzing the effects of inlet air conditions,combustor reference velocity and SMD（Sauter mean diameter） of fuel on ignition performance.

关 键 词：中心分级燃烧室 点火性能 贫油点火油气比 常温 低压 点火模型 

分 类 号：V231.2[航空宇航科学与技术—航空宇航推进理论与工程]