首页 | 本学科首页   官方微博 | 高级检索  
     检索      

富氢/富氧燃气气-气多喷嘴正交优化设计与分析
引用本文:陈涛,李茂,金平,蔡国飙.富氢/富氧燃气气-气多喷嘴正交优化设计与分析[J].航空动力学报,2011,26(9):2002-2008.
作者姓名:陈涛  李茂  金平  蔡国飙
作者单位:北京航空航天大学宇航学院,北京,100191
基金项目:国家高技术研究发展计划
摘    要:基于正交设计研究了各设计参数对富氢/富氧燃气气-气多喷嘴推力室燃烧位置、壁面温度及喷注面板温度的影响趋势和影响程度.方差分析和极差分析结果表明:燃氧速度比是影响燃烧长度和壁面温度的主要因素,较小的氧喷嘴出口厚度有利于降低喷注面板温度,但各因素的交互作用对不同设计目标影响程度差异较大;多目标响应面分析表明:低的氧喷嘴压降...

关 键 词:燃气  多喷嘴  气-气燃烧  正交设计  多目标优化设计
收稿时间:2010/10/23 0:00:00
修稿时间:2010/12/24 0:00:00

Design and analysis of GH2/GO2 fired gas multi-injectors orthogonal optimization
CHEN Tao,LI Mao,JIN Ping and CAI Guo-biao.Design and analysis of GH2/GO2 fired gas multi-injectors orthogonal optimization[J].Journal of Aerospace Power,2011,26(9):2002-2008.
Authors:CHEN Tao  LI Mao  JIN Ping and CAI Guo-biao
Institution:School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100191, China
Abstract:Orthogonal design methodology was applied to investigate the design parameters' impact on multi-objectives,including flame length,wall temperature and injector panel temperature of GH2/GO2 fired gas shear coaxial multi-injectors chamber.Variance analysis and range analysis indicate that ratio of hydrogen-rich gas velocity to oxygen-rich gas is a dominant factor for flame length and wall temperature,and small thickness of injector is beneficial for reducing injector panel temperature.The interaction effect of the design parameters varies sharply for different objectives.The result of response surface shows that low pressure drop of oxygen-rich gas,high velocity ratio and appropriate injector thickness are advantageous for balance performance.
Keywords:fired gas  multi-injectors  gas-gas combustion  orthogonal design  multi-objective optimization
本文献已被 CNKI 万方数据 等数据库收录!
点击此处可从《航空动力学报》浏览原始摘要信息
点击此处可从《航空动力学报》下载免费的PDF全文
设为首页 | 免责声明 | 关于勤云 | 加入收藏

Copyright©北京勤云科技发展有限公司  京ICP备09084417号