针栓喷注器液氧/甲烷推力室设计及试验研究  

Design and Experimental Study of Liquid Oxygen/Methane Thrust Chamber for Pintle Injector

作　　者：李军 常克宇 陈展 李纯飞 袁宇 LI Jun;CHANG Ke-yu;CHEN Zhan;LI Chun-fei;YUAN Yu(Shaanxi Land Space Aerospace Technology Co.,Ltd.,Xian 710065,China;Land Space Technology Corporation Ltd,Beijing 101762,China)

机构地区：[1]陕西蓝箭航天技术有限公司,陕西西安710065 [2]蓝箭航天空间科技股份有限公司,北京101762

出　　处：《推进技术》2022年第11期14-19,共6页Journal of Propulsion Technology

摘　　要：为了验证针栓喷注器应用于变推力液氧/甲烷推力室的可行性,探索气/液针栓喷注器的燃烧性能,设计了针栓喷注器液氧/甲烷推力室地面试验件并进行了点火试验。推力室通过两轮试验共计7次点火,单次最长点火时间200s,累计515s。结果表明,推力室可以实现液氧/甲烷的可靠点火及稳定燃烧,燃烧效率为0.959~0.979,推力室工作过程平稳,喷注器壳体及针栓的热防护措施可靠,未见烧蚀。In order to verify the feasibility of the pintle injector applied to the variable thrust liquid oxygen/methane thrust chamber and explore the combustion performance of the gas/liquid pintle injector,the ground test device of the pintle injector liquid oxygen/methane thrust chamber was designed and the ignition test was carried out.The thrust chamber passed two rounds of tests for a total of 7 times,with a maximum ignition time of 200s for a single time and a total of 515s.The results show that the thrust chamber can realize reliable ignition and stable combustion of liquid oxygen/methane,and the combustion efficiency is between 0.959~0.979.The working process of thrust chamber is stable.The thermal protection measures of injector shell and pintle are reliable and no ablation is found.

关 键 词：液体火箭发动机 推力室 液体甲烷 针栓喷注器 热试车 燃烧性能 

分 类 号：V231.1[航空宇航科学与技术—航空宇航推进理论与工程]