摘要
对两种不同的燃烧室头部(三旋流杯头部为A型、双旋流杯头部为B型)进行了研究。对有两种头部的燃烧室进行了冷态流场的数值模拟,用粒子动态分析仪(PDA)测量了两种头部的速度场和喷雾场,结合慢车工况的贫油熄火试验结果进行了分析。结果表明:A型头部喷雾的索太尔平均直径(SMD)和均匀度能满足燃烧室的性能要求,比B型头部的要好,但其贫熄特性不理想。而B型头部的贫熄特性好于A型;A型头部的内旋流器气流流通量应减小一些,以利于喷嘴端部低压区的形成,这样有可能进一步降低贫油熄火油气比。
Two kinds of combustor domes were investigated,of which one was that with three swirlers (A model),and the other with two swirlers (B model).Computation was conducted for flow field of these combustors.Flow field and fuel spray of the two designs were measured by Phase Doppler Analysis (PDA).The lean blowout fuel air ratio and flame photo were obtained.The results showed that the A model had better Sauter Mean Diameter (SMD) & uniformity than B model,but it had a worse lean blowout performance,and the flow rate in the inner swirler of A model should decrease to establish a low pressure stagnation region which would be helpful to improve the lean blowout fuel air ratio.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2004年第3期332-337,共6页
Journal of Aerospace Power
关键词
旋流杯燃烧室
流场
喷雾
贫油熄火
影响因素
航空发动机
aerospace propulsion system
combustor
aircraft engine
swirl cup
three swirlers
fuel spray
lean blowout
