摘要
基于航空发动机主燃烧室扇形试验,针对点火喷嘴特性以及火焰筒大孔射流的改变对主燃烧室性能的改善情况进行了研究。试验中进行了点火用喷嘴匹配方案对燃烧室熄火性能,以及火焰筒大孔面积变化对燃烧室贫油熄火、燃烧效率和出口温度场性能影响的研究。研究结果表明:在供油系统设计中采用放大型点火喷嘴可改善主燃烧室贫油熄火性能;增大火焰筒主燃孔的面积可提高燃烧室的燃烧效率,改善出口温度场分布,而贫油熄火特性将变差;增大掺混孔的面积可提高燃烧室的燃烧效率,改善出口温度场分布,拓宽燃烧室的熄火边界。
The effect of the ignition injector characteristic and flame tube big holes change on the combustion performance was studied based on the sector combustion testing of aeroengine. The effect of ignition injector concepts on the combustion blowout performance was investigated. The effect of big holes change for the flame tube on the combustion performance including Lean Blow-Out （LBO）, combustion efficiency and outlet temperature performance was studied. The results show that LBO is improved by amplified ignition injector. Enlarging the primary holes leads to improve the combustion efficiency and outlet temperature distribution, but leads to reduce the LBO performance, which is improved by increasing the area of dilution holes.
出处
《航空发动机》
2012年第5期13-17,共5页
Aeroengine
关键词
燃烧室
性能
扇形试验
点火喷嘴
火焰筒
主燃孔
掺混孔
航空发动机
combustion
performance
sector combustion testing
ignition injector
flame tube
primary hole
dilution holes
aeroengine
