薄膜蒸发稳定器在超级燃烧室内贫油点熄火特性  

Performances of Lean Ignition and Lean Blowout with Film Evaporation Flameholder in Hyperburner

作　　者：程晓军[1] 范育新[1] 王家骅[1] 

机构地区：[1]南京航空航天大学能源与动力学院,江苏南京210016

出　　处：《推进技术》2015年第2期246-252,共7页Journal of Propulsion Technology

基　　金：江苏省普通高校研究生科研创新计划资助项目(CXZZ12_0167)

摘　　要：为了实现涡轮基组合循环发动机燃烧室工作条件下的火焰稳定性与点火要求，首先在超级燃烧室工作条件下定性地分析了两相混气中薄膜蒸发稳定器的稳定机理和燃油蒸发过程。其次，在二元试验段内对Ma=0.1～0.4，T=450～600K的来流条件下对薄膜蒸发稳定器的贫油点火和贫油熄火性能进行试验研究。研究结果表明：相同Ma下，贫油点火当量比与贫油熄火当量比随温度的升高而降低；温度相同时，两相混气中的贫油点火当量比受燃油蒸发的影响较大。通过顺喷和逆喷两种供油方式的试验对比研究发现，雾化槽供油在较高Ma数和较高温度下具有优越的点熄火性能，能够满足涡扇冲压组合发动机燃烧室的使用要求。To achieve the requirements of the flame stability and ignition in the condition of the turbine based combined cycle hyperburner, firstly, the flame stabilization mechanism and fuel evaporation process of film evaporator flameholder were analyzed qualitatively in two phase mixtures with hyperburner operating condi-tions. Secondly,the performances of film evaporator flameholder lean ignition and lean blowout were investigated by experiment with the flow condition of Ma=0.1~0.4 and T=450~600K in the rectangular test section.The re-sults indicate that the equivalent ratio of lean ignition and lean blowout decreased with increasing temperature un-der the condition of same Mach number and it was strongly influenced by the fuel evaporation under the condition of same temperature in two phase non-premixed mixtures. In addition by comparison of upstream injection and downstream injection, it is found that evaporation notch has superior performance of ignition and blowout with the condition of high Mach number and temperature,which could satisfy the requirements of hyperburner.

关 键 词：涡轮基组合循环发动机 薄膜蒸发稳定器 当量比 停留时间 化学反应时间 燃油蒸发 

分 类 号：V236[航空宇航科学与技术—航空宇航推进理论与工程]