多喷嘴大流量气-气喷注器设计与试验  

Design and experimental study on high flowrate multi-element gas-gas injector chamber

作　　者：汪小卫[1] 高玉闪[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》2011年第10期2339-2345,共7页Journal of Aerospace Power

基　　金：国家高技术研究发展计划(2008AA702*)

摘　　要：在大流量气-气喷注器单喷嘴工况研究的基础上,为研究其在具有单元交互作用的多喷嘴工况下的燃烧特性,设计了多喷嘴推力室.喷注单元为剪切混合式单元,并具有高氢/氧速度比和氧喷嘴扩口设计,采用了能够模拟真实发动机工况的7单元同心圆排布的推力室头部结构,在对喷注单元的排布间距优化设计基础上,开展了热试车试验研究和仿真分析.结果表明所设计的喷注器在多喷嘴工况下燃烧稳定,能够在额定参数设计的燃烧室内,在SSME(space shuttle main engine)主喷注单元流量的3.7倍大流量工况下燃烧效率达到99%以上,并显示出良好的喷注器自身和带来的燃烧室身部热防护特性.To investigate the combustion characteristics of high flowrate injector in the multi-element injector chambers having interaction between the elements,based on high flowrate gas-gas injector studies in the single-element condition,a multi-element injector equipped with seven shear mixing elements was deigned,which can simulate effectively the real engine.The shear mixing element had high H_2/O_2 velocity ratio and tapered O_2 post tip.Numerical simulation and hot-fire tests were carried out with this injector using the optimal design of the injector layout.Steady operations were obtained in all these tests,and the injector showed benign heat environments on the faceplates and cylinder walls.Combustion efficiency above 99% was gotten for this injection element in the flowrate of 3.7 times of SSME（space shuttle main engine） main injection element.

关 键 词：气气燃烧 大流量 多喷嘴 全流量补燃循环 优化设计 

分 类 号：V434[航空宇航科学与技术—航空宇航推进理论与工程]