For the combustion chamber ignition in multi-startup of LOX/methane rocket engine , the development of a GOX/GCH4 spark torch igniter is required .The conceptual design was conducted and the igniter chamber pressure , igniter mixture ratio , and cooling type were determined .Ignition tests were carried out to check the ignition boundary , to obtain the performance , and to verify the continuous ignition capacity and consistency .The results showed that the design was feasible .How-ever it was found that over-heats spot existed in the spark plug surface and the flame tube after the a-nalysis of the test parts .So simulations on the ignition and combustion process were conducted and the mechanisms of the over-heat zone were determined .The directions of improvement and optimiza-tion were thus proposed .%针对液氧/甲烷发动机多次启动时推力室点火,对一种气氧/气甲烷火炬式电点火器开展了研究,进行了方案设计,确定了点火室压力、点火器混合比以及冷却方式,开展了多次点火试验,验证了气氧/气甲烷的点火混合比范围,获得了点火特性,并同时验证了多次点火能力及点火重复性,证明方案基本可行.在试验件分解后发现火花塞端面和引火管存在局部高温过热区域,对点火器点火过程以及燃烧传热过程开展仿真,确定了高温烧蚀出现的机理,并明确了结构改进优化的方向.
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