|Table of Contents|

Flow simulation of oxygen dome in thrust chamber of 25-ton LOX/LH2 expansion cycle rocket engine(PDF)

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]

Issue:
2022年01期
Page:
30-37
Research Field:
研究与设计
Publishing date:

Info

Title:
Flow simulation of oxygen dome in thrust chamber of 25-ton LOX/LH2 expansion cycle rocket engine
Author(s):
KONG Weipeng; XIE Heng
(Beijing Aerospace Propulsion Institute,Beijing 100076,China)
Keywords:
LOX/LH2 expansion cycle rocket engine;  thrust chamber;  oxygen dome;  flow uniformity;  numerical simulation
PACS:
V434.1
DOI:
-
Abstract:
In order to improve the flow uniformity of oxygen nozzle outlet in the thrust chamber of a 25-ton LOX/LH2 expansion cycle rocket engine,a three-dimensional steady-state numerical simulation of the flow field in the oxygen dome was conducted using CFD method,and the reasons for the uneven flow distribution at the outlet were analyzed. Four kinds of oxygen domes with improved structures were designed and each structure was optimized in detail. The flow field distribution in the oxygen dome and the flow distribution at the nozzle outlet were obtained by numerical simulation,and the effect of the equalizing plate and the liquid oxygen inlet structure on the flow uniformity at the nozzle outlet was analyzed. The results show that the uniformity of flow rate at the outlet can be significantly improved by adopting an expanded inlet structure to reduce the flow rate at the inlet of oxygen dome,and the relative distribution range of nozzle outlet flow is reduced from 11.97% to 4.54%. The outlet flow uniformity can be improved by increasing the orifice number and adjusting the orifice size,and the relative distribution range of nozzle outlet flow is reduced from 11.97% to 6.56%. Compared with the flat plate,the flow equalizing effect of convex plate or concave plate is worse.

References:

[1] 崔荣军,何伟锋. 25吨级膨胀循环发动机技术方案研究[J].导弹与航天运载技术,2015(6):21-24.
[2] 休泽尔. 液体火箭发动机现代工程设计[M].朱宁昌,译. 北京:中国宇航出版社,2003.
[3] 孔维鹏,丁兆波,潘亮. 燃气发生器喷注面烧蚀问题数值仿真研究[J].导弹与航天运载技术,2019(4):47-51.
[4] 丁兆波,潘刚,牛旭东,等.高压补燃大推力氢氧发动机预燃室关键技术[J].导弹与航天运载技术,2020(4):39-44.
[5] WATANABE D,IMAI K,OGAWARA A,et al. Cooling analysis for rocket engine combustion chamber with high fidelity simulation[C]//49th AIAA/ASME/SAE/ASEE Joint Propulsion Conference. Reston,Virginia:AIAA,2013.
[6] DAIDZIC N,TROPEA C,POPP M. Transient flow behavior in a rocket engine oxygen dome[C]//27th Joint Propulsion Conference. Reston,Virginia:AIAA,1991.
[7] FUKUSHIMA Y,NAKATSUZI H,NAGAO R.Development status of LE-7A and LE-5B engines for H-IIA family[J].Acta Astronautica, 2002,50(5):275-284.
[8] KOJIMA M,SUNAKAWA H,KUROSU A,et al. Preliminary design and analysis for the LE-X engine components[C]//45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. Reston,Virginia:AIAA,2009.
[9] SUNAKAWA H,OKITA K,TAMURA T,et al. Robust and optimized design for liquid rocket engine[C]//45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. Reston,Virginia:AIAA,2009.
[10] WATANABE D,IMAI K,OGAWARA A,et al. Application of high fidelity simulation to LE-X engine development[C]//47th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. Reston,Virginia:AIAA,2011.
[11] MATTSTEDT T,HENSEL C,HAIDINGER F,et al. Full scale development of advanced expander cycle thrust Chambers[C]//37th Joint Propulsion Conference and Exhibit. Reston,Virigina:AIAA,2001.
[12] MATTSTEDT T,HAIDINGER F,LUGER P,et al. Development,manufacturing and test status of the VINCI expander thrustchamber assembly[C]//38th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. Reston,Virginia:AIAA,2002.
[13] HAESELER D,HAIDINGER F,BRUMMER L,et al. Development and testing status of the vinci thrust chamber[C]//48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. Reston,Virginia:AIAA,2012.
[14] GAUFFRE M C,NEAU H,SIMONIN O,et al. Numerical simulation of dome filling in an experimental rocket engine mockup[J].Journal of Propulsion and Power,2014,30(3):617-627.
[15] 杨青真,王红梅,张银波,等.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,2005,26(6):698-701.
[16] 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(2):38-42.
WANG X L. Improved current-sharing design and experimental investigation for hydrogen chamber of gas generator[J].Journal of Rocket Propulsion,2011,37(2):38-42.
[17] 石晓波,刘占一,郭灿琳. 燃气发生器喷注器内氧腔三维流动分析[J].火箭推进,2013,39(2):6-11.
SHI X B,LIU Z Y,GUO C L. Analysis of three-dimensional flow in oxygen chamber in injector of gas generator[J].Journal of Rocket Propulsion,2013,39(2):6-11.
[18] 丁兆波,陶瑞峰,孙纪国. 大流量推力室氢头腔设计优化与数值分析[J].导弹与航天运载技术,2014(1):21-24.
[19] 宣智超,谢恒,袁宇. 某氢氧发动机推力室氢喷嘴烧蚀问题仿真分析[J].火箭推进,2016,42(5):6-11.
XUAN Z C,XIE H,YUAN Y. Simulation analysis of hydrogen nozzle ablation problem existing in thrust chamber of a hydrogen oxygen engine[J].Journal of Rocket Propulsion,2016,42(5):6-11.
[20] 王福军. 计算流体动力学分析:CFD软件原理与应用[M].北京:清华大学出版社,2004.

Memo

Memo:
-
Last Update: 1900-01-01