| 超燃冲压发动机燃烧室构型优化的试验研究 |
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| 引用本文： | 吴先宇,李小山,丁猛,刘卫东,王振国.超燃冲压发动机燃烧室构型优化的试验研究[J].国防科技大学学报,2007,29(5):1-4,47. |
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| 作者姓名： | 吴先宇 李小山 丁猛 刘卫东 王振国 |
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| 作者单位： | 国防科技大学,航天与材料工程学院,湖南,长沙,410073 |
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| 基金项目： | 国家863计划资助项目(2005AA723070) |
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| 摘 要： | 在直连式超燃冲压发动机试验系统上,通过调节超燃冲压发动机燃烧室壁面扩张角和燃料喷注位置,对燃烧室构型优化进行了试验研究。为了提高试验效率,燃烧室形面调节采用正交试验设计方法进行组织,每个形面进行5种喷注位置的试验,每次试验通过文氏管调节3个当量比的燃料流量。利用试验数据构造燃烧室性能关于构型参数的响应面模型,可用于燃烧室构型优化。通过两次渐进优化获得了性能更优的燃烧室构型,并根据试验数据分析了各构型参数对燃烧室性能的影响,结果表明:优化构型燃烧室的推力增益比基准构型增大了10.4%;燃烧室性能受各构型参数的强烈耦合影响。
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| 关 键 词： | 超燃冲压发动机 燃烧室 构型优化 直连式试验 |
| 文章编号： | 1001-2486(2007)05-0001-04 |
| 收稿时间： | 3/5/2007 12:00:00 AM |
| 修稿时间： | 2007年3月5日 |
Experimental Study of the Configuration Optimization of Scramjet Combustor |
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| WU Xianyu,LI Xiaoshan,DING Meng,LIU Weidong and WANG Zhenguo.Experimental Study of the Configuration Optimization of Scramjet Combustor[J].Journal of National University of Defense Technology,2007,29(5):1-4,47. |
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| Authors: | WU Xianyu LI Xiaoshan DING Meng LIU Weidong and WANG Zhenguo |
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| Institution: | College of Aerospace and Materials Engineering, National Univ. of Defense Technology, Changsha 410073, China;College of Aerospace and Materials Engineering, National Univ. of Defense Technology, Changsha 410073, China;College of Aerospace and Materials Engineering, National Univ. of Defense Technology, Changsha 410073, China;College of Aerospace and Materials Engineering, National Univ. of Defense Technology, Changsha 410073, China;College of Aerospace and Materials Engineering, National Univ. of Defense Technology, Changsha 410073, China |
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| Abstract: | An experimental study was conducted on the directconnect scramjet combustor experiment system to investigate the performance optimization of scramjet combustor by adjusting the shape angles and fuel injection. An orthogonal array design of experiment method was used to organize the combination of shape angles.For every combination of shape angles,five experiments with different fuel injection arrangement were carried out,and every experiment was actualized with three equivalence ratios by adjusting a throttling venturi.The test data were used to build a response surface model of the combustor performance with respect to configuration parameters for combustor configuration optimization.The optimal combustor configuration was obtained by two successive optimizations,and the effects of configuration parameters on combustor performance were analyzed.The results showed that the thrust gain of optimal combustor configuration was increased by 10.4% relative to the baseline configuration,and the combustor performance was influenced strongly by the couple of configuration parameters. |
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| Keywords: | scramjet combustor configuration optimization direct-connect test |
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