凹腔底壁喷注煤油燃料的超燃点火试验  

Experiment on ignition of kerosene in supersonic flow based on cavity floor injection

作　　者：李西鹏 刘卫东[1] 潘余[1] 刘世杰[1] 苏义[2] 

机构地区：[1]国防科学技术大学航天科学与工程学院高超声速冲压发动机技术重点实验室,长沙410073 [2]中国人民解放军总装备部驻常德地区军代室,湖南常德415000

出　　处：《航空动力学报》2016年第11期2585-2594,共10页Journal of Aerospace Power

基　　金：国家自然科学基金(91116001)

摘　　要：在来流总温为1 486K、总压为1.6MPa、马赫数为2.52的条件下,采用两级串联凹腔构型燃烧室,开展了凹腔底壁喷注煤油燃料的超燃点火试验,研究了喷嘴孔径、喷注位置对点火性能的影响.结果表明：上游凹腔底壁大孔径喷嘴喷注燃料,下游凹腔点火的方案点火性能高,在煤油总体当量比为0.102-0.206范围内均可实现成功点火与稳定燃烧;燃烧反压向上游的传播过程具有明显的滞后性且与分离区的形成过程紧密耦合;燃料喷注方案决定了煤油雾化燃料场的分布,燃料的分布特征又决定了点火特征.Experiment on ignition of kerosene injected from cavity floor in scramjet combustor with two-staged cavities were conducted at the inflow conditions of Mach number of2.52,total temperature of 1 486 K,total pressure of 1.6MPa.The influences of injector diameter and injection position on ignition ability were analyzed.Results showed that when kerosene was injected from the upstream cavity floor using large diameter injector and ignited by the spark in the downstream cavity,it led to a reliable ignition with large margin of flame stability（kerosene overall equivalent ratio range of 0.102-0.206）.The upstream propagation of pressure disturbance had an obvious hysteresis phenomenon and interacted with the formation of separating zone.The kerosene spray distribution was governed by the fuel injection scheme,and influenced the ignition characteristics on the other hand.

关 键 词：超燃冲压发动机 点火 凹腔底壁 煤油 火焰传播 

分 类 号：V235.213[航空宇航科学与技术—航空宇航推进理论与工程]