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[1]李丹琳,栾叶君,孙纪国.液氧/甲烷气液喷注器试验研究[J].火箭推进,2010,36(04):59-63.
　Experimental investigation on LOX/CH4 subscale thrust chamber[J].Journal of Rocket Propulsion,2010,36(04):59-63.
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液氧/甲烷气液喷注器试验研究

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V] 卷: 36 期数: 2010年04期 页码: 59-63 栏目: 测控与试验 出版日期: 2010-08-15
Title:
Experimental investigation on LOX/CH4 subscale thrust chamber
文章编号:
(2010)04-0059-04
作者:
李丹琳; 栾叶君; 孙纪国
北京航天动力研究所，北京 100076
Author(s):
Beijing Aerospace Propulsion Institute, Beijing 100076, China
关键词:
液氧/甲烷; 推力室; 燃烧效率; 同轴式喷嘴; 试验
分类号:
V433.9
文献标志码:
A
摘要:
介绍了液氧/甲烷气液喷注器热试验情况，试验燃烧室压力7.1~7.4MPa，混合比3.5~3.9。研究了不同的喷嘴结构参数对燃烧性能和流量特性的影响。获得了燃烧效率、流量系数、振动、点火性能以及积炭特性等重要参数。
Abstract:
The firing tests of a LOX/CH4 subscale thrust chamber are presented in this paper. The chamber pressure of the tests is between 7.1 and 7.4MPa. The mixture ratio is between 3.5 and 3.9. Effects of design parameters on the LOX/CH4 coaxial injector combustion and discharge performance are investigated by firing tests. Some key parameters are obtained such as combustion efficiency, discharge coefficient, vibration, ignition and the soot formation characteristics. The firing tests are important base for the development of a LOX/CH4 rocket engine.

参考文献/References:

[1]Heseler D, Gotz A, Frohlich A. Non-Toxic Propellants for Future Advanced Launcher Propulsion Systems[R]. AIAA 2000-3678. [2]禹天福， 李亚裕. 液氧/甲烷发动机的应用前景[J]. 航天制造技术, 2007(2): 1-5. [3]Pascal Pemple, Thomas Frohlich, Hilda Vernin. LOX/Methane and LOX/Kerosene High Thrust Engine Trade-off[R]. AIAA2001-354. [4]Wood B K. Propulsion for the 21st Century RS-68[R]. AIAA 2002-4324. [5]Tamura H, Ono F, Kumakawa A, et al. LOX/Methane Staged Combustion Rocket Combustor Investigation[R]. AIAA1987-1856. [6]孙纪国. 氢氧同轴式喷嘴流量特性试验和理论分析[J]. 航空动力学报, 2005, 20(4): 167-170． [7]孙纪国, 田昌义, 程圣清. 气液同轴直流式喷嘴喷雾及燃烧试验研究[J]. 航空动力学报, 2000, 15(3): 317-320. [8]孙纪国. 氢氧同轴式喷嘴燃烧性能试验研究[J]. 火箭推进, 2005, 31(3): 7-10． [9]Zhuang F C, Sun J G. Effects of Swirl Coaxial Injector Parameters on LOX/GH2 Engine Combustion Performance[R]. AIAA 2002-3697. [10]Haeseler D, Mading C, Gotz A, et al. Testing of LOX-Hydrocarbon Thrust Chambers for Future Reusable Launch Vehicles[R]. AIAA2002-3845. [11]Pomg Gyoo an, Seong Woong Leet, Kyoung Ho Kim. Performance Analysis of the Thrust Chamber in Liquid Rocket Engine Using Liquefied Natural Gas as a Fuel[R]. AIAA2004-3860. [12]Kyoung Ho Kim, Dae Sung Ju. Development of CHASE-10 Liquid Rocket Engine having 10tf Thrust Using LOX＆LNG(methane) [R]. AIAA2006-4907.

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备注/Memo

收稿日期：2010-０1-１2；修回日期：2010-03-02。
作者简介： 李丹琳（1982—），女，工程师，研究领域为液体火箭发动机燃烧装置设计。

更新日期/Last Update: 1900-01-01