非均匀入口与化学非平衡效应对尾喷管性能的影响研究

推进技术 ›› 2014, Vol. 35 ›› Issue (2): 166-171.

非均匀入口与化学非平衡效应对尾喷管性能的影响研究

张晓源,覃粒子,刘宇

北京航空航天大学宇航学院,北京 100191;北京航空航天大学宇航学院,北京 100191;北京航空航天大学宇航学院,北京 100191

发布日期:2021-08-15
作者简介:张晓源(1987—),男,博士生,研究领域为航空宇航推进。E-mail:zhangxiaoyuan@sa.buaa.edu.cn

Non-Uniform Entrance and Non-Equilibrium Chemical Effects on Scramjet Nozzle Performance

School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100191, China

Published:2021-08-15

摘要/Abstract

摘要： 基于煤油燃料超燃冲压发动机尾喷管,对均匀入口和非均匀入口、冻结流动模型和化学非平衡模型下的尾喷管内流动进行数值模拟,采用两方程RNG k-ε湍流模型对三维NS方程组进行求解,获得非均匀入口与化学非平衡效应对尾喷管性能的影响。计算结果表明,尾喷管内流动非均匀性由尾喷管非对称膨胀和燃烧室出口非均匀等因素构成,尾喷管入口流动参数非均匀分布对尾喷管推力、升力及俯仰力矩均有影响,算例中非均匀入口使得尾喷管净推力相对于均匀入口增加了1.2%左右；尾喷管性能受化学非平衡效应的影响,非平衡流动模型下的其净推力计算结果相对于冻结流动模型增加3%~4%。 

关键词: 超燃冲压发动机;非均匀流动;化学非平衡效应;喷管性能 

Abstract: Using frozen and non-equilibrium chemical 3D models, kerosene-fueled scramjet nozzle flow was numerically simulated with a uniform or non-uniform entrance and RNG k-ε turbulence model, in order to obtain the effects on the nozzle performance. The numerical results show that the non-uniformity of nozzle flow is composed of asymmetric expansion and non-uniform distribution in the entrance which has effects on the nozzle thrust, lift and pitching moment. Compared to the uniform entrance, the nozzle thrust increases about 1.2% with a non-uniform entrance according to the simulated results. The non-equilibrium chemical effect to the nozzle performance is visible. The numerical value of nozzle thrust with non-equilibrium chemical model is 3%~4% greater than that with frozen model. 

Key words: Scramjet；Non-uniform flow；Non-equilibrium chemical effect；Nozzle performance

张晓源,覃粒子,刘宇. 非均匀入口与化学非平衡效应对尾喷管性能的影响研究[J]. 推进技术, 2014, 35(2): 166-171.

ZHANG Xiao-yuan, QIN Li-zi , LIU Yu. Non-Uniform Entrance and Non-Equilibrium Chemical Effects on Scramjet Nozzle Performance[J]. Journal of Propulsion Technology, 2014, 35(2): 166-171.

参考文献

[1] Curran E T.Scramjet Engines:The First Forty Years[J].Journal of Propulsion and Power, 2001,7(6) .
[2] 刘兴洲.中国超燃冲压发动机研究回顾[J].推进技术, 2008,9(4):385-395.(LIU Xing-zhou.Review of Scramjet Research in China[J].Journal of Propulsion Technology, 2008,9(4):385-395.)
[3] 刘小勇.超燃冲压发动机技术[J].飞航导弹, 2003(2):38-42.
[4] Stallker R J, Truong N K, Morgan R G, et al.Effects of Hydrogen-air Non-equilibrium Chemistry on the Performance of a Model Scramjet Thrust Nozzle[J].Aeronautical Journal, 2004,(11):575-584.
[5] Mitani T, Ueda S, Tani K, et al.Validation Studies of Scramjet Nozzle Performance[J].Journal of Propulsion and Power, 1993,9(5):725-730.
[6] Schetz J A, Billig F S, Favin S.Numerical Solutions of Scramjet Nozzle Flows[J].Journal of Propulsion and Power, 1987,3(4):440-447.
[7] Schindel L.Effect of Nonuniform Nozzle Flow on Scramjet Performance[J].Journal of Propulsion and Power, 1998,5(2):363-364.
[8] Snelling S L.Effect of Nonuniform Entrance Flow Profile on Hypersonic Nozzle Pitching Moment[R].AD-A244050.
[9] 王晓栋, 乐嘉陵.入口温度剖面对喷管流场结构的影响[J].推进技术, 2002,3(4):283-286.(WANG Xiao-dong, LE Jia-ling.Effect of Temperature Profile at Entrance on Flow-Fields Nozzle[J].Journal of Propulsion Technology, 2002,3(4):283-286.)
[10] 全志斌, 徐惊雷, 李斌,等.超燃冲压发动机尾喷管非均匀进口的冷流试验与数值研究[J].航空学报,优先出版.
[11] Sangiovanni J J, Barber T J, Syed S A.Role of Hydrogen/Air Chemistry in Nozzle Performance for a Hypersonic Propulsion System[J].Journal of Propulsion Technology, 1993,9(1):134-138.
[12] Thomas L, Wolfgang W K.Computation of a Nonequilibrium Expansion Flow in a Single Expansion Ramp Nozzle[J].Journal of Propulsion Technology, 2001,7(6).
[13] 王新月, 杨振鹏, 王彦青.化学非平衡流动对超燃冲压发动机尾喷管性能的影响[J].航空动力学报, 2009,4(5):1022-1027.
[14] ZHANG Xiao-yuan, QIN Li-zi, LIU Yu.Numerical Study of Chemical Non-equilibrium Flow in Hydrocarbon Scramjet Nozzle[C].Shanghai:Proceedings of 2012International Conference on Mechanical Engineering and Material Science, 2012.
[15] 李念, 张堃元, 徐惊雷.二维非对称喷管数值模拟与验证[J].航空动力学报, 2004,9(6):802-805.
[16] 李宜敏, 张中钦, 张远君.固体火箭发动机原理[M].北京:北京航空航天大学出版社, 1999.
[17] Kundu K P, Penko P F, Yang Songlin.Reduced Reaction Mechanisms for Numerical Calculations in Combustion of Hydrocarbon Fuels[R].AIAA 98-0803.
[18] Chang J S, Lewis M J.Development of a Jet-A/ Silane/Hydrogen Reaction Mechanism for Modeling a Scramjet Combustor[R].AIAA 99-2252.
[19] 黄生洪, 徐胜利, 刘小勇.煤油超燃冲压发动机两相流场数值研究[J].推进技术, 2005,6(2).(HUANG Sheng-hong, XU Sheng-li, LIU Xiao-yong.Combustion Flow of Kerosene-Fueled Scramjet with 3D Cavity[J].Journal of Propulsion Technology, 2005,6(2).)