| 超音速燃烧实验研究(Ⅰ) |
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| 引用本文： | 刘兴洲,刘敬华,王裕人,葛运圻,杨丽新.超音速燃烧实验研究(Ⅰ)[J].推进技术,1991(2). |
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| 作者姓名： | 刘兴洲 刘敬华 王裕人 葛运圻 杨丽新 |
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| 作者单位： | 航空航天部三十一所
(刘兴洲，刘敬华，王裕人，葛运圻)，航空航天部三十一所(杨丽新) |
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| 基金项目： | 国家自然科学基金资助项目 |
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| 摘 要： | 用电弧加热空气,对带有突扩台阶的扩张形超燃冲压发动机燃烧室进行了实验研究.燃烧室入口Ma=2.1,总温、总压分别约为1200K和0.7MPa.燃料以垂直或平行于气流的方式喷射,采用氢气或煤油,均能在广宽的当量比范围内稳定燃烧.同时,也比较了它们的燃烧状况.
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| 关 键 词： | 超音速燃烧 试验 研究 |
EXPERIMENTAL INVESTIGATION ON SUPERSONIC COMBUSTION(I) |
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| Liu Xingzhou Liu Jinghou,Wang Yuren Ge Yunqi Yang Lixin.EXPERIMENTAL INVESTIGATION ON SUPERSONIC COMBUSTION(I)[J].Journal of Propulsion Technology,1991(2). |
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| Authors: | Liu Xingzhou Liu Jinghou Wang Yuren Ge Yunqi Yang Lixin |
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| Institution: | The 31st Research Institute |
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| Abstract: | The experimental investigation with a model scramjet combu-stor which consists of rearward-facing step and diverging duct was carried out by using electric arc-heated air to simulate combustor inlet Mach number 2.1, total pressure0.7MPa and total temperature1200K.The fuel was injected parallelly or perpendicularly to the airstream. Both kerosene and hydrogen csn burn steadily within a wide range of fuel-air equivalence ratio, and their combustion state was compared. |
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| Keywords: | Supersonic combustion Test Research |
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