| 氢在超音速气流中的燃烧过程 |
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| 引用本文： | 杨爱国,刘陵,王宏基.氢在超音速气流中的燃烧过程[J].航空动力学报,1991,6(3):271-272,287. |
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| 作者姓名： | 杨爱国 刘陵 王宏基 |
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| 作者单位： | 1.西安航空航天部计算技术研究所 |
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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： | 氢燃料超音速燃烧冲压发动机(简称超燃冲压)为主体的吸气式组合动力装置,已被证明是空天飞机推进器的最佳方案1]。因而研究氢在超音速气流中的燃烧过程是一个重要的课题。国外近年来进行了大量的有关理论与实验研究工作2、3],但大多数的研究停留在氢处于静止与等压状态下的反应过程。在超燃燃烧室中的实际燃烧过程,由于不同的燃烧室进口气流状态,大体有以下三种基本类型:扩散型燃烧、扩散动力型燃烧、动力型燃烧。
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| 收稿时间： | 9/1/1990 12:00:00 AM |
COMBUSTION PROCESSES OF HYDROGEN IN A SUPERSONIC AIR FLOW |
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| Yang Aikuo,Liu Ling and Wang Hongji.COMBUSTION PROCESSES OF HYDROGEN IN A SUPERSONIC AIR FLOW[J].Journal of Aerospace Power,1991,6(3):271-272,287. |
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| Authors: | Yang Aikuo Liu Ling and Wang Hongji |
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| Institution: | 1.Computing Technical Research Institute2.Northwestern Polytechnic University |
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| Abstract: | According to the implicit numerical integration method proposed by Tyson.J,an improved computer program for pseudo one dimensional flow of combustion kinetics is developed with the aid of a chemical kinectic model with 12 species and 31 reaction.Variations of temperature,prssure,Mach number and mass fraction of chemical species in a supersonic combustion model are studied in detail.The results of scramjet combustor conditions corresponding to flight Mach numbers 6,10 and 15 show that chemical reaction rates decrease at rather low temperature and pressure at a combustor inlet and there is not enough time to ignite the mixture gas in the combustor at very high Mach number,in result the performance limits of scramjet kinetic combustion occur. |
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