底排装置尾部化学非平衡流的数值模拟

推进技术 ›› 2015, Vol. 36 ›› Issue (11): 1610-1615.

底排装置尾部化学非平衡流的数值模拟

余文杰,余永刚

南京理工大学能源与动力工程学院，江苏南京 210094,南京理工大学能源与动力工程学院，江苏南京 210094

发布日期:2021-08-15
作者简介:余文杰(1986—)，男，博士生，研究领域为底排装置尾部流场的数值模拟。
基金资助:
国家自然科学基金项目(51176076)。

Numerical Simulation of Base Flow with Chemical

Department of Power Engineering，Nanjing University of Science & Technology，Nanjing 210094，China and Department of Power Engineering，Nanjing University of Science & Technology，Nanjing 210094，China

Published:2021-08-15

摘要/Abstract

摘要： 为了研究二次燃烧对底排增压减阻的影响，采用8组分12步反应的H2-CO燃烧模型作为二次燃烧模型，运用统一算法的思路编程求解二维轴对称多组分N-S方程，对底排装置尾部化学非平衡流进行数值模拟。底排装置的底压随排气参数变化的模拟结果和现有实验数据比较吻合。数值模拟结果表明:底排装置底部压力随着排气参数I的增加先迅速增大，当I达到0.007时，底压增长速度逐渐变慢，在I=0.01～0.015的范围内底压基本不变，此时底排增压减阻的效果最好。当排气温度Tj≤1025K时，底排装置尾部没有发生二次燃烧，底排减阻率相对较小。当1025K1100K时，二次燃烧充分。底排装置的排气温度应大于1100K。

关键词: 流体力学；底部排气；二次燃烧；数值模拟；尾部流场；化学非平衡流

Abstract: In order to investigate the effects of the secondary combustion on the drag reduction rate of base bleed，a H2-CO combustion model which consists 8 components and 12 reactions was used for the secondary combustion simulations. Two-dimensional axisymmetric equations were programmatically computed using a set of uniform numerical process methods. The base flow with chemical non-equilibrium of base bleed was simulated. The base pressure of the base bleed equipment with different injection parameters of the simulations were basically in agreement with the experimental data. The results show that the base pressure of the base bleed equipment first increases rapidly with the increase of the injection parameters I. When the injection parameters I reaches 0.007，the growth of the base pressure gradually slows. When I=0.01～0.015，the base pressure is basically unchanged with the increase of the I，and the effect of drag reduction with base bleed is best. When the injection temperature Tj≤1025K，the drag reduction rate of base bleed is relatively small，because the secondary combustion has not happened in the base region of the base bleed equipment. When 1025K1100K，the secondary combustion is complete. The injection temperature of the base bleed equipment should be larger than 1100K.

Key words: Fluid mechanics；Base bleed；Secondary combustion；Numerical simulation；Base flow field；Chemical non-equilibrium flow

余文杰,余永刚. 底排装置尾部化学非平衡流的数值模拟[J]. 推进技术, 2015, 36(11): 1610-1615.

YU Wen-jie,YU Yong-gang. Numerical Simulation of Base Flow with Chemical[J]. Journal of Propulsion Technology, 2015, 36(11): 1610-1615.

参考文献

[1] 郭锡福. 底部排气弹外弹道学[M]. 北京:国防工业出版社, 1995.
[2] 丁则胜, 邱光纯, 刘亚飞, 等. 固体燃料底部排气空气动力研究[J]. 空气动力学学报, 1991, 9(3): 300-307.
[3] Mathur T, Dutton J C. Base Bleed Experiments with a Cylindrical Afterbody in Supersonic Flow[J]. Journal of Spacecraft and Rockets, 1996, 33(1): 30-37.
[4] Bourdon C J, Dutton J C. Visualization of a Central Bleed Jet in an Axisymmetric Compressible Base Flow[J]. Physics of Fluids, 2003, 15(2): 499-510.
[5] Bowman J E, Clayden W A. Cylindrical Afterbodies at M=2 with Hot Gas Ejection[J]. AIAA Journal, 1968, 6(12): 2429-2431.
[6] 丁则胜, 罗荣, 陈少松, 等. 底部燃烧减阻性能的若干参数影响研究[J]. 弹道学报, 1996, 8(4): 79-83.
[7] Sahu J, Heavey K R. Numerical Investigation of Supersonic Base Flow with Base Bleed[J]. Journal of Spacecraft and Rockets, 1997, 34(1): 62-69.
[8] Shin J R, Cho D R, Won S H, et al. Hybrid RANS/LES Study of Base-Bleed Flows in Supersonic Mainstream[R]. AIAA 2008-2588.
[9] Shin J R, Choi J Y. DES Study of Base and Base-Bleed Flows with Dynamic Formulation of DES Constant[R]. AIAA 2011-662.
[10] 陈新虹, 黄华, 周志超, 等. 排气能量对底部排气弹气动特性影响的数值模拟[J]. 兵工学报, 2010, 31(4): 447-452.
[11] Gibeling H J, Buggeln R C. Projectile Base Bleed Technology Part 1: Analysis and Results[R]. AD A258-459, 1992.
[12] Choi J Y, Shin E, Kim C K. Numerical Study of Base-Bleed Projectile with External Combustion[R]. AIAA 2005-4352.
[13] 罗盟, 武晓松, 封锋, 等. 底排装置底部压力和回流区特性研究[J]. 推进技术, 2013, 34(3): 347-352. (LUO Meng, WU Xiao-song, FENG Feng, et al. Numerical Investigation on Base Pressure and Recirculation Region Characteristics of Base Bleed Device[J]. Journal of Propulsion Technology, 2013, 34(3): 347-352.)
[14] 卓长飞, 武晓松, 封锋. 底部排气弹三维湍流燃烧的数值模拟[J]. 固体火箭技术, 2013, 36(6): 720-726.
[15] 卓长飞, 武晓松, 封锋. 超声速流动中底部排气减阻的数值研究[J]. 兵工学报, 2014, 35(1): 18-26.
[16] Menter F R. Two-Equation Eddy-Viscosity Turbulence Models for Engineering Application[J]. AIAA Journal,1994, 32(8): 1598-1605.
[17] 武频, 赵润祥, 郭锡福. 弧长网格生成法及其应用[J]. 南京理工大学学报, 2002, 26(5): 482-485.
[18] 刘君, 张涵信, 高树椿. 一种新型的计算化学非平衡流动的解耦方法[J]. 国防科技大学学报, 2000, 22(5): 19-22.
[19] 梁德旺, 王可. AUSM+格式的改进[J]. 空气动力学学报, 2004, 22(4): 404-409.
[20] Yoon S, Jameson A. Lower-Upper Symmetric Gauss-Seidel Method for the Euler and Navier-Stokes Equations[J]. AIAA Journal, 1988, 26(9): 1025-1026.(编辑:张荣莉)　　　　　　　　　　　　　*　收稿日期:2014-07-22；修订日期:2014-09-26。基金项目:国家自然科学基金项目(51176076)。作者简介:余文杰(1986—),男,博士生,研究领域为底排装置尾部流场的数值模拟。E-mail: spacecow@sina.com