气氧/甲烷同轴剪切喷注器燃烧特性数值模拟  

Numerical simulation on the combustion characteristic of shear coaxial GO_2/ GCH_4 injector

作　　者：高玉闪[1] 杜正刚[1] 金平[1] 蔡国飙[1] 

机构地区：[1]北京航空航天大学宇航学院,北京100191

出　　处：《火箭推进》2009年第5期18-23,33,共7页Journal of Rocket Propulsion

摘　　要：对以气氧/甲烷为推进剂的同轴剪切喷注器进行了数值模拟,研究了喷注器设计参数对推进剂掺混燃烧、燃烧室壁面和喷注面板热载的影响。研究结果表明:氧喷注速度增大不利于推进剂的掺混燃烧,降低了燃烧效率,增大了燃烧室壁面和喷注面板的热载;动量比增大提高了推进剂的燃烧效率,缩短了燃烧距离,但增大了燃烧室壁面和喷注面板的热载;中心氧喷嘴管壁厚和氧喷嘴管的缩进,对燃烧效率有影响,但两者对燃烧室壁面和喷注面板热载影响不明显;对燃烧效率而言,特定情况下氧喷嘴缩进存在一最佳值。Numerical simulation of shear coaxial GO2/GCH4 injector is conducted to study the effects of the design parameters on the combustion characteristics and the heat flux of the wall and faceplate. The results show that increasing the oxygen injected velocity is harmful to mixing and combustion and makes the combustion efficiency decreased and the heat flux of the wall and faceplate increased. Higher momentum ratio enhanced the mixing and the combustion and made a short combustion length. The higher the combustion efficiency, the higher the heat flux of the wall and faceplate. The thickness and recess of the gas oxygen post had influence on the combustion efficiency, but less influence on the heat flux of the wall and faceplate. The recess of the gas oxygen post existed an optimum value on the combustion efficiency.

关 键 词：气氧/甲烷喷注器 设计参数 燃烧效率 温度 数值模拟 

分 类 号：V434[航空宇航科学与技术—航空宇航推进理论与工程]