单喷嘴大流量气-气喷注器设计与试验  

Design and experiment of high flowrate single-element gas-gas injectors

作　　者：汪小卫[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,北京100191

出　　处：《航空动力学报》2010年第3期691-698,共8页Journal of Aerospace Power

基　　金：国家863高科技基金(2007AA702);北京航空航天大学博士创新基金(430569)

摘　　要：首先对典型单喷嘴氢/氧同轴剪切式喷注器燃烧流场进行了仿真计算,分析了其燃烧流场特性;并在同轴剪切式构型基础上,为增强掺混、缩短燃烧长度、以适用于大流量工况,进行了改进设计以及相应的数值模拟和试验研究.结果表明:具有高氢/氧动量比和氧喷嘴扩口设计的同轴喷注器可以有效地缩短燃烧长度,并具有良好的热载环境,能够适用于大流量工况.研究结果为设计高效率、可靠热防护的大流量气-气喷注器的设计打下基础,并提供设计思路.The GH2/GO2 combustion flow field in a chamber with a single element typi cal shear coaxial injector was numerically simulated firstly. The characteristics of the flow field and the shear coaxial injector architecture were analyzed to enhance the mixing and decrease the combustion length, some improved designs were made for suiting high flowrate conditions. Numerical analysis and validation experiments were conducted for single-element chambers with these injectors. The improved shear mixing element with high H2/O2 velocity ratio and a flared O2 post tip could maintain a benign heat load environment, and effectively enhance the GH2/GO2 mixing suitable for the combustion in the nominal combustor with high injection flowrate. The results directly contribute to the high flow rate gas-gas injector design and the design methodologies in this paper give references for further studies.

关 键 词：大流量喷注器 全流量补燃循环 掺混 燃烧长度 

分 类 号：V434[航空宇航科学与技术—航空宇航推进理论与工程]