航天推进技术研究院主办
[1]郭敬,孔凡超,张家仙,等.发动机试验富燃气体安全处理技术发展综述[J].火箭推进,2017,43(06):1-6.
GUO Jing,KONG Fanchao,ZHANG Jiaxian,et al.Development of fuel-rich gas safety treatment technology for engine test[J].Journal of Rocket Propulsion,2017,43(06):1-6.
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GUO Jing,KONG Fanchao,ZHANG Jiaxian,et al.Development of fuel-rich gas safety treatment technology for engine test[J].Journal of Rocket Propulsion,2017,43(06):1-6.
发动机试验富燃气体安全处理技术发展综述
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
43
期数:
2017年06期
页码:
1-6
栏目:
专论与综述
出版日期:
2017-12-30
- Title:
- Development of fuel-rich gas safety treatment technology for engine test
- 文章编号:
- 1672-9374(2017)06-0001-06
- Keywords:
- rocket engine test; safety treatment; inert gas blowdown; active combustion; passive combustion
- 分类号:
- V433.9-34
- 文献标志码:
- A
- 摘要:
- 首先介绍了液体火箭发动机试验过程富燃气体的排出方式以及安全处理的必要性。文中总结了国内外最具代表性的液体火箭发动机试验冷氢排放处理所采用的高空排放、 火炬烟囱和燃烧池三种不同方式的特点、工作原理和典型试验台的应用情况。重点介绍了惰性气体吹除、被动燃烧和主动燃烧三种富燃燃气安全处理方式及不同富燃燃气处理方式在不同试验台的应用情况。所总结的液体火箭发动机试验过程富燃气体安全处理相关技术可为大推力氢氧发动机试验台燃气安全处理研究提供借鉴。
- Abstract:
- The necessity of fuel-rich gas exhausting mode and safety treatment during liquid rocket engine test is introduced. The key characteristics, operating principle and typical test bed application of high-altitude exhaust, flare stack and burning pool used for the most representative chilled hydrogen exhaust treatment at home and abroad in the process of liquid rocket engine test are summarized. Three fuel-rich gas safety treatment ways of inert gas blowdown, active combustion and passive combustion implied to different test beds are introduced emphatically. The fuel-rich gas safety treatment technologies used in the process of liquid rocket engine test are helpful to the safety treatment research of large thrust LOX/LH2 rocket engine test bed.
参考文献/References:
[1] 符锡理.国外火箭技术中氢的安全排放与处理[J].国外导弹与宇航, 1981(12): 23-27.
[2] LAPIN A. Hydrogen vent flare stack performance[J]. Advances in cryogenic engineering, 1967, 12: 198-206.
[3] ГАЛЕЕВ А Г.火箭发动机研制与试验中的生态安全问题[M]. 莫斯科: 莫斯科航空学院, 2006.
[4] BARTT H, JOHN L. Hydrogen reclamation and reutilization: NP-2009-09-00164- SSC[R]. [S.l.]: [s.n.], 2009.
[5] MENDEZ G, DRAKE R, CARLILE J. Large liquid engine test facility: AIAA 2001-0608[R]. Reston: AIAA, 2001.
[6] THOMPSON W R, BONCORE C S. Design and development of a test facility for the disposal of hydrogen at high flow rates[J]. Advances in cryogenic engineering, 1967(12): 207-217.
[7] 何常勇.某新型靶场液氢排放燃烧系统设计构想[J].低温工程, 2010(6): 41-45.
[8] SMITH R K, CHRISTENSEN E R, WAGNER D A. Development of a dual propulsion test capability for the RS68 engine at NASA Stennis Space Center: AIAA 99-2166[R], Reston: AIAA, 1999.
[9] SAUNDERS G P. Design, activation, and operation of the J-2X subscale simulator: AIAA 2009-5098[R]. Res-ton: AIAA, 2009.
[10] VINEET A, ASHVIN H, ANDREA Z, et al. Computational analyses in support of sub-scale diffuser testing for the A-3 facility Part 2: unsteady analyses and risk assessment: AIAA 2009-5205[R]. Reston: AIAA, 2009.
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备注/Memo
收稿日期:2016-10-31
作者简介: 郭敬(1979—),女,博士,高级工程师,研究领域为液体火箭发动机试验技术
更新日期/Last Update:
1900-01-01