摘要
为探究不同旋流器位置和数目对航空发动机燃烧室性能的影响规律,运用FLUENT软件,采用计算流体力学法对某旋转流线涡燃烧室冷态流场和燃烧性能进行了研究。结果表明:相比于其他位置,旋流器距离燃烧室头部为88 mm时流线涡更稳定、更不易脱落,且燃烧效率最高,火焰长度也最短,燃烧效果最理想;旋流器数量的改变对压力损失和火焰长度的影响并不明显,但3个旋流器产生的涡范围更大,且会使空气与燃料掺混得更好,壁面温度场更加理想,燃烧性能更好。
In order to investigating the effect of installation location and amount on combustor performance of aeroengine,the cold flow field and combustion performance in revolving streamline vortex combustor were analyzed by the software FLUENT and CFD（Computational Fluid Dynamics） method.The results show that when distance between swirl cup and the top of combustor is 88mm,vortex is better,combustion efficiency is the highest and length of flame is the shortest.Effect of amount of swirl cup on pressure loss and length of flame are inconspicuous.But the scope of vortex,wall temperature and combustion performance of tri-swirl are better than the dual-swirl.
出处
《航空发动机》
2014年第2期76-80,共5页
Aeroengine
基金
中央高校基本科研业务费专项资金(HEUCF120303)资助
关键词
旋转流线涡
燃烧室
冷态流场
燃烧性能
旋流器
燃气轮机
航空发动机
revolving streamline vortex
combustor
cold flow field
combustion performance
swirl cup
gas turbine
aeroengine
