基于凹槽火焰稳定器的煤油超声速燃烧试验  

Experimental investigation of kerosene supersonic combustion based on cavity flameholder

作　　者：王辽[1] 韦宝禧[1] 章成亮[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：《北京航空航天大学学报》2008年第8期907-910,共4页Journal of Beijing University of Aeronautics and Astronautics

摘　　要：在直联式超声速燃烧试验台上进行了煤油的超声速燃烧试验，使用了4种不同结构的凹槽火焰稳定器和多种直径的煤油喷嘴，煤油当量比0．24～1．32，引导氢当量比0．53，在多种工况下均实现了煤油的成功点火和稳定燃烧．通过测量燃烧室壁面静压分布比较不同工况下煤油燃烧性能．研究发现：凹槽结构对煤油的点火性能影响较大，较大的凹槽长深比更有利于煤油的点火，部分凹槽能在无引导氢条件下实现煤油自燃点火；试验中使用的4种凹槽均有较好的火焰稳定效果，煤油燃烧时燃烧室壁面压力平稳；煤油当量比是影响煤油燃烧性能的最主要因素．在煤油当量比相同的条件下，较高的喷注压力能够提高煤油的燃烧性能．Experimental investigation of kerosene supersonic combustion was performed on direct-connect supersonic combustion test facility by using four different configurations of cavity flameholders and multi-diam- eter kerosene injectors. Kerosene equivalence ratio varies from 0.24 to 1.32 and polite hydrogen equivalence ratio was 0.53. Successful ignition and sustain combustion were achieved in multi-test conditions. The distri- bution of wall static pressure was measured to validate the combustion performances under different test conditions. The experimental results show the four cavity flameholders used in the test have excellent flame holding effects. The configuration of cavity has great influence on the ignition of kerosene in supersonic airstream. Larger length depth ratio was better for the kerosene ignition, and with several cavities, kerosene can achieve self- ignition without pilot hydrogen, equivalence ratio is the most important influencing factor of kerosene combustion capabilities. At same kerosene equivalence ratio, higher injection pressure can improve the kerosene combustion effects.

关 键 词：冲压发动机 超声速燃烧 煤油 凹槽火焰稳定器 

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]