| 高超声速吸气发动机燃气模拟装置 |
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| 引用本文： | 陈宏,李斌,李进平,单希壮,董志成,吴松,俞鸿儒.高超声速吸气发动机燃气模拟装置[J].空气动力学学报,2009,27(Z1). |
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| 作者姓名： | 陈宏 李斌 李进平 单希壮 董志成 吴松 俞鸿儒 |
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| 作者单位： | 中国科学院力学研究所,北京,100190 |
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| 基金项目： | 中国科学院交叉学科项目和国家自然科学基金资助项目 |
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| 摘 要： | 本文阐述了用于提高冲压发动机在高马赫数飞行条件下的推力,而发展的简单可靠的催化复合效应实验研究所需要高温燃气的产生方法;进行了理论分析与数值计算;成功研制了一座能产生高温空气与气态燃料燃烧产物的高温燃气激波风洞实验装置,并得到了压力为20大气压,温度为3200K,定常实验时间约为17ms且状态参数稳定的实验结果.
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| 关 键 词： | 爆轰驱动 激波管 冲压发动机 催化复合 |
Apparatus to produce high-temperature gas for simulating hypersonic propulsion |
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| CHEN Hong,LI Bin,LI Jin-ping,SHAN Xi-zhuang,DONG Zhi-cheng,WU Song,YU Hong-ru.Apparatus to produce high-temperature gas for simulating hypersonic propulsion[J].Acta Aerodynamica Sinica,2009,27(Z1). |
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| Authors: | CHEN Hong LI Bin LI Jin-ping SHAN Xi-zhuang DONG Zhi-cheng WU Song YU Hong-ru |
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| Abstract: | In an effort to increase the thrust of scramjet engines at high Math numbers, a method was developed to produce high - temperature gas for catalysis. Theoretical analyses and numerical calculations were conducted and a shock tunnel to produce mixtures of high - temperature air and gas - fuel was built. Reproducible results were obtained at 3200 K and a total pressure of 2 MPa. The experimental time approached 17 ms. |
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| Keywords: | detonation driven shock tube scramjet catalysis |
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