氢氧火箭发动机高模试验富氧蒸汽引射仿真  

Simulation of oxygen-rich steam ejection in high altitudesimulation test for hydrogen/oxygen rocket engine

作　　者：张小通 李茂[1,2] 张家仙 刘瑞敏[1,2] ZHANG Xiaotong;LI Mao;ZHANG Jiaxian;LIU Ruimin(Beijing Institute of Aerospace Testing Technology,Beijing 100074,China;Beijing Engineering Research Center of Aerospace 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]北京市航天试验技术与装备工程技术研究中心,北京100074

出　　处：《火箭推进》2023年第2期100-106,共7页Journal of Rocket Propulsion

基　　金：国家留学基金(CSC201804980019);宇航动力领域项目(2020KGWYY4316Tm)。

摘　　要：氢氧火箭发动机在高空模拟试验中喷出富氢燃气,其中的残余氢气与倒吸进引射系统中的空气混合容易发生爆炸,为研究富氧蒸汽引射处理氢氧火箭发动机高空模拟试验中残余氢气的技术,采用计算流体力学(CFD)及多步化学反应动力学模型开展单级环形超—超引射器仿真,获得富氧蒸汽引射的平均流场,分析富氧蒸汽引射并发生补燃时超—超引射器的稳态工作特性,并考察富氧蒸汽中氧气含量、富氧蒸汽温度对残余氢气处理效果的影响。仿真结果表明,富氧蒸汽引射并发生补燃时环形引射器在稳态下正常工作;补燃主要发生在引射器混合室和第二喉道前端的剪切混合层;增大富氧蒸汽的氧气含量或温度,可使引射器排气中残余氢气含量降低,增强燃气处理效果。During high altitude simulation test,hydrogen-rich gas is jetted out from hydrogen-oxygen rocket engine,where the residual hydrogen mixed with air backed up into the ejection system may explode.To study the technology of oxygen-rich steam ejection to treat the residual hydrogen in the high altitude simulation of hydrogen-oxygen rocket engine,the single-stage annular supersonic-supersonic ejector simulation was carried out using computational fluid dynamics and multi-step chemical reaction kinetics model to obtain the oxygen-rich steam ejection mean flow field.Analyzing the working characteristics of the ejector in the steady state,and the effects of oxygen concentration in oxygen-rich steam and steam temperature on the treatment of residual hydrogen were also investigated.The simulation results show that the annular ejector works normally in steady state when using oxygen-rich steam to inject.Afterburning occurs mainly in the shear mixing layer at the mixing chamber and the front section of the ejector.When the oxygen concentration or temperature of the oxygen-rich steam is increased,it can reduce the concentration of hydrogen in the exhaust gas of the ejector and enhance the treatment effect of hydrogen-rich gas.

关 键 词：氢氧发动机 高空模拟试验 超—超引射器 富氧蒸汽引射 燃气处理 

分 类 号：V433.9[航空宇航科学与技术—航空宇航推进理论与工程]