基于正交设计的气-气喷嘴数值模拟  

Numerical simulation of gas-gas injector based on orthogonal design

作　　者：杜正刚[1] 高玉闪[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,100191

出　　处：《航空动力学报》2009年第6期1396-1401,共6页Journal of Aerospace Power

基　　金："863"高技术项目(2006AA702305)

摘　　要：通过应用正交表安排喷嘴的主要参数以进行设计,并对以气氢/气氧为推进剂的同轴剪切喷嘴进行数值模拟.选择燃烧位置为评价喷嘴性能的参数,研究单喷嘴质量流量、氧喷嘴压降、速度比和氧喷嘴出口角度对喷嘴的燃烧位置的影响.通过对数值模拟的结果的极差和方差分析表明:增大流量使推进剂的燃烧位置远离喷注面,流量是对燃烧位置影响程度最大参数;提高速度比使燃烧位置与喷注面距离缩短,而氧压降和氧喷嘴出口角度变化对燃烧位置的影响较小.The numerical simulation was performed on gaseous oxygen/gaseous hydro gen shear coaxial injector as orthogonal array was applied to guide injector design. The injec tor combustion location was selected as the indicator of injector performance. The effect of injector mass flowrate, oxygen pressure drop, the hydrogen to oxygen velocity ratio as well as the angle of oxygen post tip on the combustion length were investigated. The range analysis and variance analysis on the results of numerical simulation indicate that the increase of injector mass flowrate make the combustion location far away from the injector faceplate, injector mass flow plays a predominated role in combustion location; and a higher velocity ratio of hydrogen to oxygen shortens the distance between the combustion location and the injector faceplate; the oxygen element drop and the angle of oxygen post tip have minimum impact on combustion location.

关 键 词：燃烧位置 同轴剪切喷嘴 数值模拟 正交表 

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]