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针栓喷注器液氧/甲烷推力室设计及试验研究
李军1,常克宇1,陈展1,李纯飞1,袁宇2
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 100176
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。
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
DOI:10.13675/j.cnki.tjjs.210570
分类号:V231.1
基金项目:
Design and Experimental Study of Liquid Oxygen/Methane Thrust Chamber for Pintle Injector
LI Jun1, CHANG Ke-yu1, CHEN Zhan1, LI Chun-fei1, YUAN Yu2
1.Shaanxi Landspace Aerospace Technology Co.,Ltd.,Xi’an 710065,China;2.Land Space Technology Co.,Ltd.,Beijing 100176,China
Abstract:
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.
Key words:  Liquid rocket engine  Thrust chamber  Liquid methane  Pintle injector  Hot fire test  Combustion performance