摘要
对回流燃烧室设计了两种主燃孔结构(交错射流和对齐射流),在不同压力条件下对不同主燃孔方案的回流燃烧室的点火性能进行了试验研究.试验结果表明:随着回流燃烧室进口空气压力的降低,点火边界的油气比先减小后升高,而对齐主燃孔的火焰筒方案的低压点火性能优于交错主燃孔.结合火焰筒冷态流场数值模拟和试验中观察到的点火现象进行对比分析,对齐主燃孔方案存在更大范围的回流区,其火焰筒头部参考速度较低.此方案有利于减弱火焰核心的淬熄概率,同时增强头部火焰燃烧的稳定性,从而改善了回流燃烧室的点火性能.
Two structures of primary holes （staggered jets and aligned jets） were de- signed for reverse-flow liner. Experiments were conducted to study the combustor ignition performance affected by two structures of primary holes at different pressure conditions. The experiment result indicates that as the inlet air pressure of the reverse-flow combustor de- creases, the fuel/air ratio at ignition boundary decreases at first and then increases. The ig- nition performance of aligned jets primary holes is better than that of staggered jets primary holes. Combined with numerical simulation results of liner cold flow field and ignition phe- nomena observed in the experiment, the area of recirculation zone is expanded and reference velocity of the liner is reduced due to the aligned jets primary holes. It is beneficial for de- creasing the quenching probability of flame kernel and enhancing the stability of the flame. Thus ignition performance of the reverse-flow combustor is improved.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2015年第5期1057-1066,共10页
Journal of Aerospace Power
关键词
主燃孔
轴向位置
回流燃烧室
低压
点火性能
primary holes
axial position
reverse-llow combustor
low pressure
ignition per{ormance
