摘要
为研究富氢/富氧燃气同轴双剪切气-气喷嘴设计参数对燃烧性能和燃烧室热载的影响,采用正交试验设计方法对这些参数进行组合,数值模拟单喷嘴燃烧室流场,并以燃烧长度、燃烧室壁面和喷注面板处平均燃气温度为指标评价燃烧性能和热载.结果表明:燃氧速度比对燃烧性能和燃烧室热载影响最显著,中心氢流量比例对燃烧室热载影响非常显著,氧压降比对喷注面板处燃气平均温度的影响也很显著,而喷嘴出口壁厚对喷嘴性能影响不明显.燃氧速度比和氧压降比的交互作用对喷嘴性能有一定影响,而其他设计参数之间的交互作用对喷嘴性能影响非常小.最短燃烧室长度为117.9mm,最低壁面燃气温度及面板燃气温度分别为1 637.7K和806.6K.
To study the influence of the design parameters of a hydrogen-rich/oxygen-rich shear tricoaxial gas-gas injector on the combustion performance and the heat load performance,the parameters were fitted combination through the orthogonal experiment design method.The flow field of the single injector combustor was simulated.Evaluation indexes were the combustion length,the average gas temperature on combustion chamber wall and the average gas temperature on the injection faceplate.The results show that the fuel velocity to the oxidizer velocity has the most remarkable influence on the combustion performance and the heat load performance,the percentage of the central fuel mass flow rate has very obvious impact on the heat load performance,and the ratio of the oxidizer pressure drop to the combustor pressure has notable influence on the faceplate temperature,while the oxidizer post tip wall thickness has insignificant influence on the performance of the injector.To some extent,the interaction between the velocity ratio and oxidizer pressure drop affects the performance of the injector,while other interactions of the design parameters have little influence.The shortest combustion length is 117.9 mm.The lowest wall temperature is 1 637.7 K,and faceplate temperature is 806.6 K.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2013年第6期1380-1386,共7页
Journal of Aerospace Power
基金
国家高技术研究发展计划
关键词
同轴双剪切气-气喷嘴
喷嘴设计参数
数值仿真
正交试验设计
燃烧性能
燃烧室热载
shear tricoaxial gas-gas injector
injector design parameters
numerical simulation
orthogonal experiment
combustion performance
combustion chamber heat load
作者简介
姜金朋（1988-），女，山东莱阳人，博士生，主要从事可重复火箭发动机研究．
