应用气泡雾化喷嘴的煤油超声速燃烧试验  

Experimental investigation of kerosene supersonic combustion test using aerated-liquid injectors

作　　者：王辽[1] 章成亮[1] 韦宝禧[1] 徐旭[1] 

机构地区：[1]北京航空航天大学宇航学院,北京100191

出　　处：《航空动力学报》2009年第2期353-359,共7页Journal of Aerospace Power

摘　　要：在直联式超声速燃烧试验台上应用气泡雾化喷嘴,煤油当量比0.97和0.33分别使用氢气、空气和氮气为起泡气体进行了煤油超声速燃烧试验.在多种工况下实现了煤油的稳定燃烧.研究发现:凹槽火焰稳定器通过制造高温低速漩涡区增加煤油在燃烧室内的停留时间,并使煤油得到充分加热从而实现煤油的点火和稳定燃烧.通过气泡雾化喷嘴加入少量氢气,由于氢气进入燃烧室后迅速自燃释放热量,能够提高煤油的燃烧性能,使得煤油能够在无凹槽火焰稳定器的条件下稳定燃烧.Experimental investigation of kerosene supersonic combustion was performed on direct-connect supersonic combustion test facility by using aerated-liquid injectors. In the test, kerosene equivalence ratio was 0.97 and 0.33, and hydrogen, air and nitrogen were used as effervescent gas respectively. The experimental results show that, cavity flameholders can achieve kerosene self-ignition and flame-holding effect by producing an eddy with low speed and high temperature, kerosene can prolong the resident time in eombustor and achieve sufficient heating by the effect of this eddy. The hydrogen can self-ignite and release energy while injecting into the supersonic combustor, therefore adding hydrogen by aerated-liquid injector can improve the combustion performance of kerosene, and even achieve stable combustion without cavity flameholder.

关 键 词：超声速燃烧 气泡雾化喷嘴 凹槽火焰稳定器 超燃冲压发动机 

分 类 号：V434.13[航空宇航科学与技术—航空宇航推进理论与工程]