大流量气-气喷嘴响应面法优化设计  

Large mass flowrate gas-gas injector optimization design with response surface methodology

作　　者：杜正刚[1] 李茂[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

出　　处：《北京航空航天大学学报》2010年第4期395-398,共4页Journal of Beijing University of Aeronautics and Astronautics

基　　金：国家863基金资助项目

摘　　要：为研究以气氢和气氧为推进剂的同轴双剪切喷嘴设计参数对推进剂燃烧位置的影响,利用正交表指导喷嘴设计,并对燃烧室流场进行数值模拟.结果表明:在单喷嘴流量相当于航天飞机主动发动机单喷嘴流量8倍的工况下,同轴双剪切喷嘴能实现高的燃烧效率;极差和方差分析显示氢/氧的速度比是对推进剂的燃烧位置影响最大的设计参数,而中心氢流量比例和氧喷嘴的壁厚对燃烧位置的影响不显著.通过构造基于正交多项式的响应面,获得同轴双剪切气-气喷嘴的优化组合参数.In order to investigate the effect of design parameters of dual shear coaxial injector that utilizes gaseous oxygen and hydrogen as propellants on the combustion location,the numerical simulation efforts were performed to simulate the flow field of combustor with orthogonal array applied to guide the injector design.The results display that dual shear coaxial injector made propellants combusted efficiently at the condition of large mass flowrate which was close to eight times greater than that of space shuttle main engine（SSME） single element injector.The range analysis and variance analysis indicate that the velocity ratio of hydrogen to oxygen has significant effect on the combustion location,while the ratio of center hydrogen mass fraction and oxygen wall thickness have not influenced the combustion location significantly.The response surface methodology based on orthogonal-polynomial is employed to get the optimized parameters of the dual shear coaxial injector.

关 键 词：燃烧 效率 优化 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]