应用气动谐振的气氧、煤油点火器的方案研究

俞南嘉; 张国舟; 马彬

应用气动谐振的气氧、煤油点火器的方案研究

北京航空航天大学宇航学院, 北京 100083

基金项目: 航天科技创新基金2000年资助项目

详细信息

作者简介:
俞南嘉(1974-),男,浙江镇海人,博士生,yunj@buaa.edu.cn.

中图分类号: V 431
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- 被引次数: 0
出版历程
- 收稿日期: 2002-07-11
- 网络出版日期: 2003-09-30

Investigation on methods of kerosene/oxygen ignition using gas dynamic resonance technique

School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100083, China

摘要

摘要: 为了实现液体推进剂火箭发动机的多次可靠起动,将气动谐振点火技术应用于气氧煤油的点火.提出了两种应用气动谐振的气氧煤油点火器方案:直接点火方案和间接点火方案.在直接点火方案中对气氧与煤油同轴喷入和煤油由顶部喷入两种不同的点火方式进行了分析比较.在间接点火方案中对点火火炬为富燃和富氧两种情况进行了对比分析.试验研究表明两种方案均实现了多次可靠的点火并生成了稳定的点火火炬.通过对两种方案的优缺点、工程上应用的技术可行性和存在的技术难点的分析,认为富燃情况的间接点火方案具有明显的优势并有望在短期内达到工程应用要求.
- 点火装置 /
- 谐振腔 /
- 液体推进剂火箭发动机
Abstract: In order to realize the multiple ignitions of liquid rocket engines reliably, gas dynamic resonance ignition was applied to ignite kerosene/oxygen. Two ignition methods of kerosene/oxygen igniter, direct ignition and indirect ignition, were discussed. For direct ignition method, the differences between the co-axial injection of kerosene/oxygen and the top injection of kerosene were compared. For indirect ignition method, the condition of fuel-rich ignition torch was studied in contrast with the condition of fuel-lean ignition torch. Accordingto the analysis of technical feasibility and difficulty, it can be concluded from experiments that both methods are valid for ignition, while indirect ignition method with fuel-rich torch has more advantages and is prospective to realize in engineering application within a short term.
- ignition device /
- resonators /
- liquid rocket engines

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参考文献(1)

[1] Niwa M, Kessaev K, Santana J A, et al. Development of a resonance igniter for GO₂/kerosene ignition. AIAA 2000-3302, 2000 [2] Rocketdyne Engineering. Advanced ignition systems final report. N71-35152, 1972 [3] 张国舟,童晓艳,梁国柱,等. 液体火箭发动机气动谐振点火技术的研究. 宇航学报, 2001, 22(4):81~84 Zhang Guozhou, Tong Xiaoyan, Liang guozhu, et al. Investigation on gas dynamic resonance ignition technology for liquid propellant rocket engine[J]. Journal of Astronautics, 2001, 22(4):81~84(in Chinese) [4] 梁国柱,张振鹏,张国舟,等. 气动谐振管加热机理数值研究[J]. 北京航空航天大学学报,1999,25(6):692~695 Liang Guozhu, Zhang Zhenpeng, Zhang Guozhou,et al. Numerical investigation of gasdynamic resonance tube heating[J]. Journal of Beijing University of Aeronautics and Astronautics, 1999, 25(6):692~695(in Chinese) [5] 童晓艳,马彬,张国舟,等. 塞式喷管发动机多管点火方案的研究 [J]. 宇航学报, 2001, 22(4):62~66 Tong Xiaoyan, Ma Bin, Zhang Guozhou,et al. Investigation on the ignition methods of aerospike nozzle engine[J]. Journal of Astronautics, 2001, 22(4):62~66(in Chinese)

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