富氢/富氧燃气同轴直流喷嘴燃烧过程数值模拟  

Numerical simulation of combustion for GH_2/GO_2 gas-fired shear coaxial injector

作　　者：李茂[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：《北京航空航天大学学报》2010年第4期469-473,共5页Journal of Beijing University of Aeronautics and Astronautics

基　　金：国家863基金资助项目

摘　　要：为研究全流量补燃FFSC(Full Flow Staged Combustion)循环发动机气-气喷注器性能,以气氢/气氧(GH2/GO2)预燃室提供的758K富氢燃气和676K富氧燃气为推进剂对同轴直流喷嘴燃烧流场进行了数值模拟.考察了相同燃烧室结构、流量、入口燃气温度条件下,富氧燃气压降、富氢燃气和富氧燃气的速度比、氧喷嘴厚度和氧喷嘴缩进变化对燃烧性能的影响,获得了4个参数的影响规律.数值模拟结果对燃气气-气喷注器结构设计有参考价值.To research the performance of the gas-fired injector in full flow staged combustion（FFSC） cycle engine,a gas-fired shear coaxial injector was simulated to obtain the performance of combustion.The gaseous hydrogen and gaseous oxygen（GH2/GO2） preburners were utilized to provide the hydrogen-rich gas at the temperature of 758 K and the oxygen-rich gas at the temperature of 676 K.It was performed to analyze the influence of the oxygen-rich gas pressure drop,the ratio of hydrogen-rich gas velocity to oxygen-rich gas velocity,the thickness of oxygen-rich gas injector and the recess of oxygen-rich gas injector on combustion performance.All the operating condition have the same structure of chamber,mass flux,gas-fired temperature.Influence of the four parameters were obtained.The results provide reliable criterion for the design of gas-gas shear coaxial injector.

关 键 词：燃气 同轴直流喷嘴 数值模拟 

分 类 号：V434.13[航空宇航科学与技术—航空宇航推进理论与工程]