热沉式燃烧室热载分析  

Investigation on the heat flux of heat sink chamber

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：《航空动力学报》2010年第11期2619-2624,共6页Journal of Aerospace Power

基　　金：国家高技术研究发展计划(2009AA7020504)

摘　　要：采用了以紫铜为材料的热沉式燃烧室身部设计,测量了不同氢/氧速度比下同轴剪切气-气喷注器燃烧室壁面的温度分布和燃烧室压力,分析了不同速度比下推进剂的特征速度效率和燃烧室壁面温度分布的不同,计算了沿燃烧室轴向的热流强度和燃烧室吸热量占推进剂完全反应所应释放能量的比例分数.研究方法对工程应用具有参考价值.The wall temperature and pressure in cooper heat sink chamber were measured under different velocity ratios of hydrogen to oxygen during hot fire tests of the shear-coaxial injector.The characteristic velocity efficiency and temperature distribution of the chamber wall were analyzed,and the heat flux distribution along the axial direction of the chamber and the quantity of heat absorbed by the chamber were calculated;and the proportion of the energy released for the propellant was computed.The method provides useful insight into the engineering applications.

关 键 词：热沉式燃烧室 气-气喷注器 速度比 壁面温度 热流密度 

分 类 号：V434[航空宇航科学与技术—航空宇航推进理论与工程]