氢氧火箭发动机试验低温氢气燃烧处理装置研究  

Research of Cryo-GH2 Active Combustion Device for LOX/LH2 Rocket Engine Tests

作　　者：方维[1,2] 张伟 FANG Wei;ZHANG Wei(Beijing Institute of Aerospace Testing Technology, Beijing 100074, China;Beijing Engineering Research Center of Aerospace Propulsion Testing Technology and Equipment, Beijing 100074, China)

机构地区：[1]北京航天试验技术研究所,北京100074 [2]北京市航天动力试验技术与装备工程技术研究中心,北京100074

出　　处：《传感器世界》2019年第8期7-12,共6页Sensor World

摘　　要：针对大推力氢氧火箭发动机试验富氢起动、富氢关机时排出的低温氢气安全处理问题,本文采取数值模拟结合工程试验的方式,设计氢氧火箭发动机试验低温氢气燃烧处理装置。装置以常温氢气火炬主动燃烧的方式处理环境中积聚的低温氢气,并以氮气引流的方式隔绝氢气,阻止氢气、燃气扩散。此方案在多个型号的发动机整机试验及动力系统试验中得到了成功的应用,具有较高的可靠性。In this paper, an active combustion device is designed by adopting the method of numerical simulation combined with engineering experiment, to solve the problem of safety disposal of cryo-GH2 discharged from high-thrust LOx/LH2 rocket engine during hydrogen-rich starting and hydrogen-rich shutdown. This system treats the cryo-GH2 accumulated in the environment by means of active combustion of normal-temperature hydrogen torch, and prevents the diffusion of hydrogen and gas by means of nitrogen drainage. This scheme has been successfully applied in various types of rocket engines tests and large launch vehicle's stage tests.

关 键 词：氢氧火箭发动机试验 安全处理 低温氢气 主动燃烧装置 

分 类 号：V553.21[航空宇航科学与技术—人机与环境工程]