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为了研究氢气自燃辅助乙烯点火的具体点火参数和点火性能,在直连式脉冲燃烧风洞设备上进行了模拟飞行马赫数4条件下的超燃发动机乙烯点火试验,试验来流的总温935K,总压0.8MPa,隔离段入口马赫数2.1。试验利用不同质量流量的引导氢气自燃辅助点火,成功实现了乙烯燃料的点火和稳定燃烧。通过流场显示和壁面压力测量发现:(1)能够成功点火的引导氢气流量范围为0.43~12.61g/s,相当于当量比0.005~0.142;(2)0.43g/s流量氢气注入燃烧室后10ms以内被点燃,乙烯燃料注入后经过了约20ms才被点燃,点火的主要位置为凹槽内;(3)6.68g/s的氢气注入燃烧室后20ms才被点燃,乙烯燃料注入后约8ms即被点燃,点火的主要位置为凹槽下游和凹槽出口位置;(4)点火试验中火焰能够在凹槽内和剪切层内向上游逆传;(5)凹槽下游和下壁面的燃烧,是促进凹槽内燃烧、提升燃烧室压力和引起燃烧室压力震荡的主要原因。
In order to study the specific ignition parameters and ignition performance of hydrogen ignition assisted ethylene ignition, the ignition test of the engine of the super-combustion engine under simulated flight Mach number 4 was carried out on a direct-fired pulsed combustion wind tunnel equipment. The total temperature of the test stream was 935K, Total pressure 0.8MPa, isolation section entrance Mach 2.1. The pilot uses different mass flow to guide hydrogen auto-ignition to assist ignition, and successfully achieves the ignition and stable combustion of ethylene fuel. Through the flow field display and wall pressure measurement, it is found that: (1) The flow rate of hydrogen gas that can be successfully ignited is 0.43 ~ 12.61g / s, equivalent to the equivalent ratio of 0.005 ~ 0.142; (2) 0.43g / (3) 6.68 g / s of hydrogen was injected into the combustion chamber after 20ms was ignited, about 8ms after the injection of ethylene fuel into the combustion chamber (4) In the ignition test, the flame can reverse upstream within the groove and the shear layer; (5) The combustion at the downstream and the lower wall of the groove , Is to promote the combustion groove, to enhance the pressure of the combustion chamber and the main reason for causing pressure oscillations in the combustion chamber.