基于火焰面模型的推力室起动过程仿真

推进技术 ›› 2013, Vol. 34 ›› Issue (3): 362-367.

基于火焰面模型的推力室起动过程仿真

初敏¹,徐旭¹,许晓勇²

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;北京航天动力研究所,北京100076

发布日期:2021-08-15
作者简介:初敏(1985—),男,博士生,研究领域为航空宇航推进理论与工程。 E-mail:chumin@sa.buaa.edu.cn

Numerical Simulation on Start-up Process in Thrust Chamber Based on Flamelet Model

School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;Beijing Aerospace Propulsion Institute, Beijing 100076, China

Published:2021-08-15

摘要/Abstract

摘要： 采用计算流体力学的方法,对氢氧火箭发动机推力室的起动过程进行了数值仿真。起动的非定常过程由双时间步方法模拟,燃烧过程由稳态层流火焰面模型模拟,火焰面建库采用6组分8步反应的化学动力学模型。按照地面试车时序进行推力室起动过程仿真,获得了起动过程的建压曲线以及详细的流场建立过程。结果表明,经过点火瞬间压力松弛控制的稳态层流火焰面模型可用于火箭发动机的点火过程动态仿真,仿真得到的压力曲线与试车曲线相比符合良好。 

关键词: 火箭发动机;起动过程;火焰面模型;数值仿真 

Abstract: Numerical simulation on start-up process in thrust chamber of hydrogen-oxygen rocket engine was performed by computational fluid dynamics method. Dual-time-step method and steady laminar flamelet model were utilized to simulate the unsteady process and combustion process, respectively. The database of flamelet model was set up by 8steps with 6specices chemical reaction model. The pressure curve and the detailed parameters of flowfield were achieved from the simulation, which was performed according to the time sequence of start-up process. It turns out that, the steady laminar flamelet model is available to the start-up process and the pressure curve shows good consistency with the test curve. 

Key words: Rocket engine; Start-up process; Flamelet model; Numerical simulation

初敏,徐旭,许晓勇. 基于火焰面模型的推力室起动过程仿真[J]. 推进技术, 2013, 34(3): 362-367.

CHU Min¹, XU Xu¹,XU Xiao-yong². Numerical Simulation on Start-up Process in Thrust Chamber Based on Flamelet Model[J]. Journal of Propulsion Technology, 2013, 34(3): 362-367.

参考文献

[1] 张小平.补燃循环发动机起动过程仿真研究[J].火箭推进,2003,29(3):18-21.
[2] 苏龙斐,张黎辉,潘海林.卫星推进系统发动机启动过程数值仿真[J].航空动力学报,2005,20(4):698-701.
[3] 李家文,张黎辉,张雪梅,等.空间推进系统静动态特性仿真软件研究[J].推进技术,2004,25(2):148-151.(LI Jia-wen,ZHANG Li-hui,ZHANG Xue-mei,et al.Simulation Software of the Static and Dynamic Characteristics of Space Propulsion System[J].Journal of Propulsion Technology,2004,25(2):148-151.)
[4] 王昕.流量调节器动态特性研究[J].火箭推进,2004,30(3):19-24.
[5] 白晓瑞.液体火箭推进系统动态特性仿真研究[D].长沙:国防科学技术大学,2009.
[6] 潘辉,张黎辉.AMESim软件在液体火箭发动机系统动态仿真上的应用[J].火箭推进,2011,37(2):6-11.
[7] 丰松江,聂万胜,车学科,等.氢氧发动机湍流两相燃烧三维全尺寸数值仿真[J].系统仿真学报,2011,23(1):52-55.
[8] 李强,聂嵩,刘业奎,等.过氧化氢/煤油发动机推力室气液燃烧数值模拟[J].火箭推进,2011,37(4):35-39.
[9] 刘卫东,王振国,周进,等.液体火箭发动机切向不稳定燃烧数值分析模型[J].推进技术,1998,19(1):16-19.(LIU Wei-dong,WANG Zhen-guo,ZHOU Jin,et al.A Numerical Analysis Model of Tangential Combustion Instability in Liquid Propellant Engine[J].Journal of Propulsion Technology,1998,19(1):16-19.)
[10] 刘卫东,王振国,周进,等.火箭发动机燃烧室内气体非定常流动数值模拟[J].国防科技大学学报,1996,18(3):11-15.
[11] 张澄宇,孙晓峰.加力燃烧室流场形态与振荡燃烧数值模拟[J].航空动力学报,2010,25(2):270-277.
[12] Menter F R.Two Equation Eddy Viscosity Turbulence Models for Engineering Applications [J].AIAA Journal,1994,32: 1598-1605.
[13] Liou M S.Mass Flux Schemes and Connection to Shock Instability [J].Journal of Computational Physics,2000,160: 623-648.
[14] Van Leer B.Towards the Ultimate Conservation Difference Scheme V:A Second-Order Sequal to Godunov''s Method [J].Journal of Computational Physics,1979,32:101-136.
[15] 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.
[16] Jamenson Antony.Time Dependent Calculations Using Multigrid with Application to Unsteady Flows Past Airfoils and Wings[R].AIAA 91-1596.
[17] Peters N.Laminar Diffusion Flamelet Models in Non-Premixed Turbulent Combustion[J].Progress in Energy and Combustion Science,1984,10:319-339.
[18] Clutter J K,Mikolaitis D W,Shyy W.Effect of Reaction Mechanism in ShockInduced Combustion Simulations [R] .AIAA 98-0274.