多喷管液体火箭动力系统尾焰流场特性研究

推进技术 ›› 2017, Vol. 38 ›› Issue (2): 356-363.

多喷管液体火箭动力系统尾焰流场特性研究

乔野,聂万胜,丰松江,吴高杨

装备学院航天装备系，北京 101416,装备学院航天装备系，北京 101416,装备学院航天装备系，北京 101416,装备学院航天装备系，北京 101416

发布日期:2021-08-15
作者简介:乔野，男，硕士生，研究领域为液体火箭发动机。
基金资助:
国家自然科学基金(51206185；91441123)。

Research on Plume Flow-Field Characteristics of Multi-Nozzle Rocket Propulsion System

Department of Space Equipment，Equipment Academy，Beijing 101416，China,Department of Space Equipment，Equipment Academy，Beijing 101416，China,Department of Space Equipment，Equipment Academy，Beijing 101416，China and Department of Space Equipment，Equipment Academy，Beijing 101416，China

Published:2021-08-15

摘要/Abstract

摘要： 为深入研究多喷管液体火箭动力系统尾焰流场特性，以由10台液体火箭发动机组成的多喷管动力系统为模型，采用耦合了Realizable k-ε湍流模型的N-S方程描述尾焰流动过程，考虑复燃反应的影响，并运用压力的隐式算子分割(PISO)算法进行求解，实现了以液氢液氧和液氧煤油为推进剂的两种不同发动机尾焰的混合计算，得到了不同飞行高度下火箭动力系统的尾焰流场结构及其参数分布情况。结果表明:随着飞行高度的升高，尾焰的膨胀角度越来越大，尾焰间的相互作用加强。由于复燃反应及尾焰间相互作用影响，尾焰流场会出现局部高温区域，同时火箭底部及喷管周围会出现旋流，旋流会卷吸尾焰高温燃气，从而会对火箭底部进行烧蚀，需要对其采取相应的热防护措施。

关键词: 液体火箭发动机；多喷管；复燃反应；尾焰；数值仿真

Abstract: In order to take more research about plume flow-field characteristics of multi-nozzle rocket propulsion system consisted of ten liquid rocket engines，the N-S equations coupled with Realizable k-ε model are used to describe the flow process. The PISO algorithm is used to solve the N-S equations and the effect of afterburning is considered in the simulation. The coupling simulation of [LH2]/LOX engine and LOX/kerosene engine exhaust plume is accomplished. The plume flow-field structure and parameter distribution of rocket exhaust plume at different altitude are acquired. The simulation results indicate that with increasing the flight altitude，the expansion angle of plume increases and the interaction between plumes is enhanced. Because of the effect of afterburning and interaction between plumes，partial high temperature regions will occur in the flow-field. Besides，reversed flow is formed around the after-body of the rocket and nozzles. The reversed flow can bring the hot exhaust and heat up the air around the after-body. So the thermal protection should be taken at these places.

Key words: Liquid rocket engine；Multi-nozzle；Afterburning；Plume；Numerical simulation

乔野,聂万胜,丰松江,吴高杨. 多喷管液体火箭动力系统尾焰流场特性研究[J]. 推进技术, 2017, 38(2): 356-363.

QIAO Ye,NIE Wan-sheng,FENG Song-jiang,WU Gao-yang. Research on Plume Flow-Field Characteristics of Multi-Nozzle Rocket Propulsion System[J]. Journal of Propulsion Technology, 2017, 38(2): 356-363.

参考文献

[1] 世界航天运载器大全编委会. 世界航天运载器大全[M]. 北京:宇航出版社,1996.
[2] 苗瑞生. 发射气体动力学[M]. 北京:国防工业出版社, 2006.
[3] Hideyo N, Nobuhiro Y, Makoto A, et al. Numerical Analysis of Plume Heating Environment for H-IIA Launch Vehicle during Powered Ascent[R]. AIAA 2007-5505.
[4] Ze-Juan Xiao, Hui-Er Cheng. Plume Interaction in Parallel Multi-Thrusters Propulsion System and the Effect on Backflow[R]. AIAA 2006-3599.
[5] Houshang B E. Numerical Investigation of Multi-Plume Rocket Phenomenology[R]. AIAA 1997-3622.
[6] 胡声超, 李昂, 鲍福廷, 等. 多喷管燃气降噪方案可行性数值研究[J]. 固体火箭技术, 2012, 35(2):198-202.
[7] 孙萍, 范新运. 多喷管火箭发动机尾流场流动与辐射特性的数值模拟分析[J]. 机电一体化, 2008, 14(7): 41-44.
[8] 王雁鸣, 谈和平, 董士奎, 等. 低空多喷管发动机喷焰红外研究[J]. 固体火箭技术, 2009, 32(6): 634-637.
[9] 聂万胜, 丰松江. 液体火箭发动机燃烧动力学模型与数值计算[M]. 北京:国防工业出版社, 2011.
[10] 聂万胜, 杨军辉, 何浩波, 等. 液体火箭发动机尾喷焰红外辐射特性[J]. 国防科技大学学报, 2005, 27(5):91-94.
[11] 丰松江, 聂万胜, 解庆纷, 等. 燃烧室内燃烧模型对尾焰流场及其辐射的影响[J]. 火箭推进, 2006, 32(2): 6-10.
[12] 丁兆波, 孙纪国, 路晓红. 国外典型大推力氢氧发动机推力室技术方案综述[J]. 导弹与航天运载技术, 2012(4): 27-30, 38.
[13] 谭永华. 大推力液体火箭发动机研究[J]. 宇航学报, 2013, 34(10): 1303-1308.
[14] 李东, 程堂明. 中国新一代运载火箭发展展望[J]. 中国航天, 2008(2): 7-10.
[15] 吴子牛. 空气动力学[M]. 北京:清华大学出版社, 2008.
[16] 蔡红华, 聂万胜, 丰松江. 复燃对液氧煤油发动机尾焰冲击特性影响[J]. 推进技术, 2016, 37(9). (CAI Hong-hua, NIE Wan-sheng, FENG Song-jiang. The Effect of Afterburning on the Impact Characteristics of LOX/Kerosene Rocket Engine Plume[J]. Journal of Propulsion Technology, 2016, 37(9).)
[17] 陶文铨. 数值传热学[M]. 西安:西安交通大学出版社, 1988.
[18] Songjiang FENG, Yufeng CHENG, Wansheng NIE. Combustion Instability Analysis in a Hydrogen-Oxygen Rocket Engine[R]. AIAA 2009-4864.
[19] 李茂, 王占林. 氢氧火箭发动机射流仿真与试验台热防护[J]. 载人航天, 2014, 20(5): 421-426.　收稿日期:2015-08-18；修订日期:2015-10-29。基金项目:国家自然科学基金(51206185；91441123)。作者简介:乔野,男,硕士生,研究领域为液体火箭发动机。E-mail: jony322@126.com(编辑:史亚红)