摘要
燃油逆向喷射改变了传统航空发动机的燃烧室头部喷射燃油和旋流稳定燃烧的燃烧组织方式,它利用高温燃气回流区内的高温低氧条件,实现稳定高效超低污染的MILD燃烧模式。通过改变逆向燃油喷嘴不同喷射位置和不同喷射角度,模拟分析了对MILD燃烧方式和燃烧性能的影响。当喷嘴取合适的位置和喷射角度等燃烧参数时,能实现基于来流空气温度的MILD燃烧方式,以及高品质出口温度场、超低NO x排放等优良燃烧性能。研究结果对新概念航空发动机设计具有参考价值。
Fuel reverse injection has changed the traditional aero-engine combustion methods of fuel injec- tion at combustor head and swirl combustion stability, which utilizes high temperature and lowers oxygen content conditions within flue gas recirculation zone to achieve MILD combustion mode of stabilization, high efficiency and ultra-low pollute emissions. This paper simulated and analyzed the effects on MILD combus- tion mode and combustion performances by changing the nozzle locations and angles of reverse injection. When the combustion parameters of nozzle location and angle are appropriate, MILD combustion mode based on the inlet air temperature and excellent combustion performances of high quality outlet temperature fields, ultra-low NOx emission can be achieved. All results correspond to other similar findings and have ref- erence values to new concept aeroengine design.
出处
《沈阳航空航天大学学报》
2013年第5期10-15,共6页
Journal of Shenyang Aerospace University
基金
航空科学基金资助项目(项目编号:20112B54005)
关键词
航空发动机
逆向喷射
MILD燃烧
燃烧性能
数值研究
aeroengine
reverse injection
MILD combustion
combustion performance
numerical research
