航天推进技术研究院主办
[1]王晓丽.燃气发生器氢腔均流改进设计及试验研究[J].火箭推进,2011,37(02):38-42.
WANG Xiao-li.Improved current-sharing design and experimental investigation for hydrogen chamber of gas generator[J].Journal of Rocket Propulsion,2011,37(02):38-42.
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WANG Xiao-li.Improved current-sharing design and experimental investigation for hydrogen chamber of gas generator[J].Journal of Rocket Propulsion,2011,37(02):38-42.
燃气发生器氢腔均流改进设计及试验研究
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
37
期数:
2011年02期
页码:
38-42
栏目:
研究与设计
出版日期:
2011-04-15
- Title:
- Improved current-sharing design and experimental investigation for hydrogen chamber of gas generator
- 文章编号:
- 1672-9374(2011)02-0048-05
- 分类号:
- V434-34
- 文献标志码:
- A
- 摘要:
- 为解决某型号液体火箭发动机燃气发生器热试车后氢腔内过滤网和骨架的破损问题，在不改变燃气发生器功能和性能、不影响发动机其它系统功能的前提下，设计了七种均流替代方案。采用Navies-Stokes方程数值模拟七种方案的氢腔内流动状态，计算分析了各种方案的氢喷嘴流量的均匀性，综合考虑承载能力，选定了一种有较好均流效果的均流环。对改进后的燃气发生器进行了液流试验和热试车考核。液流试验表明，改进后的燃气发生器氢路压降与改进前吻合，热试车后均流环无异常。分析和试验验证表明，新设计的均流环能起到均匀氢喷嘴流量的作用，提高了抵抗起动压力峰的能力，增加了燃气发生器的工作可靠性。
- Abstract:
- To solve the problem of cracking of the filter-screen and skeleton within hydrogen chamber of the gas generator after test of certain liquid rocket engine, seven current-sharing schemes are designed on the premise that the function and performance of the generator are not reduced. Through the calculation, analysis and simulation of the fluid dynamic status, flow uniformity and intensity of the seven design schemes, a current-sharing design with better structural intensity is chosen. Hydraulic test and test-driving are carried out for the modified generator successfully. The results manifest that the novel current-sharing design can play a role of sharing the flux of the hydrogen injector elements, enhance the capability of anti-startup pressure peak, and consequently, improve the stability of the generator.
参考文献/References:
[1]SANFORD Gordon, BONNIE J McBcide. Computer program for calculation of complex chemical equilibrium compositions, rocket performance, incident and reflected shocks and Chapman-Jouguet detonations, N73-17724[R]. [S. l.]: [s. n.], 1973.
[2]NICHOLLS J A, WILKINSON H R, MORRISON R B. Intermittent detonation as a thrust producing mechanism [J]. Jet Propulsion, 1957, 27: 534-541.
[3]陈旭扬. 燃气发生器起动压力峰研究[J]. 航天推进与动力, 2007, 4(1): 1-4.
[4]李清廉, 李庆, 王振国. 氧气/醇类燃气发生器起动过程试验研究[J]. 火箭推进, 2010, 36 (1): 13-18.
[5]王福军. 计算流体动力学分析[M]. 北京: 清华大学出版社, 2005.
[6]杨青真, 王红梅, 张银波. 液体火箭发动机氧腔流动分析及均流板设计研究[J]. 宇航学报, 2005, 6 (26): 698-701.
[7]石亦平, 周玉蓉. Abaqus有限元分析实例详解[M]. 北京: 机械工业出版社, 2005.
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备注/Memo
收稿日期：2010-11-11；修回日期：2011-01-06
作者简介： 王晓丽（1983—），女，工程师，研究领域为液体火箭发动机推力室设计
更新日期/Last Update:
1900-01-01