复合式收扩套筒空气雾化喷嘴燃烧室点火研究  

Research on ignition performance of a hybrid airblast atomizer combustor with convergent-divergent sleeve

作　　者：林宇震[1] 林培华[1] 许全宏[1] 刘高恩[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重点实验室,北京100083

出　　处：《航空动力学报》2007年第3期342-346,共5页Journal of Aerospace Power

摘　　要：复合式收扩套筒空气雾化喷嘴中，副油路是一个单油路离心喷嘴，主油路采用双旋流空气雾化，喷嘴是直射式．在点火研究中，只是单油路离心喷嘴工作．实验用的燃烧室是一个单头部矩形燃烧室，在燃烧室进口温度为常温，进口压力为常压，燃烧室压力降0．9％～9．0％的试验条件下研究了复合式空气雾化喷嘴燃烧室的点火性能．在同样条件下，研究了复合式空气雾化喷嘴的雾化性能并总结了经验关系．分析了影响点火的主要因素，通过整理雾化数据，以Lefebvre点火模型为基础，总结了该类燃烧室点火经验关系．For a hybrid airblast atomizer combustor with convergent-divergent sleeve, a simplex pressure swirl nozzle is used for the primary fuel circuit, and a direct-injection airblast atomizer is used for the main fuel circuit. Only the pilot simplex nozzle was operated in the ignition tests. The test comhustor is a single-nozzle rectangular comhustor, with normal inlet temperature and normal inlet pressure. Under the test condition of pressure drop of 0. 9%-9.0%, the ignition performance of hybrid airblast atomizer combustor was analyzed. And, the atomization performance of this hybrid atomizer was also summarized to obtain the empirical correlation under the same condition. While major influential factors to ignition were analyzed, the empirical correlation of such combustors was summarized based on the atomization data and Lefebvre＇s ignition model.

关 键 词：航空 航天推进系统 航空发动机 燃烧室 点火 复合式空气雾化喷嘴 模型 

分 类 号：V211.6[航空宇航科学与技术—航空宇航推进理论与工程] V231.1