燃气喷射推力矢量喷管气固两相流数值模拟
Numerical simulation of gas-particle flow in hot gas injection thrust vector nozzle
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摘要: 利用Euler-Lagrangian方法模拟了固体火箭发动机燃气喷射推力矢量喷管气固两相内流场,研究了固体颗粒对喷管推力矢量性能的影响.气相采用Roe格式和MUSCL (monotone upstream-centred schemes for conservation laws)插值进行空间2阶迎风离散,时间推进采用隐式时间格式;固体颗粒相采用随机轨道模型计算颗粒轨迹,并与气相进行双向耦合.结果表明:固体颗粒的存在使弓形激波强度增强,但降低了推力矢量角和推力系数;颗粒质量分数相同时,粒径越大,推力矢量角和推力系数越大;颗粒直径相同时,颗粒质量分数越大,推力矢量角和推力系数越小.Abstract: The gas-particle inner flowfield of gas injection thrust vector nozzle in solid rocket engine was simulated using Euler-Lagrangian method,and the effect of solid particle on thrust vector performance was studied.The Roe scheme and monotone upstream-centred schemes for conservation laws(MUSCL)method were used for secondary-order accuracy spatial discretization for gas phase,and the implicit scheme was employed for time marching.The stochastic trajectory model and two-way coupled with gas phase were employed for particle phase.The results indicate that the strength of bow shock is increased due to solid particles,but the thrust vector angle and thrust coefficient are decreased;thrust vector angle and thrust coefficient increase with the particle diameter increasing under the same mass fraction of particle condition;thrust vector angle and thrust coefficient decrease with the mass fraction of particle increasing under the same particle diameter condition.
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[1] 林飞,王根斌.固体火箭发动机推力向量控制[M].北京:国防工业出版社,1981. [2] Deere K A.Summary of fluidic thrust vectoring research conducted at NASA Langley Research Center .AIAA 2003-3800,2003. [3] Kowal H J.Advances in thrust vectoring and the application of flow-control technology[J].Canadian Aeronautics and Space Journal,2002,48(2):145-151. [4] 张相毅,王如根,徐学邈,等.二元喷管流体矢量控制方案数值研究[J].航空动力学报,2007,22(9):1435-1438. ZHANG Xiangyi,WANG Rugen,XU Xuemiao,et al.Computational analysis of fluidic vector control concepts for binary nozzle[J].Journal of Aerospace Power,2007,22(9):1435-1438.(in Chinese) [5] 雷金春,金捷.激波诱导轴对称气动矢量喷管流场数值模拟[J].航空动力学报,2008,23(9):1585-1590. LEI Jinchun,JIN Jie.Numerical simulation of flow-field for shock induced axisymmetric fluidic vectoring nozzle[J].Journal of Aerospace Power,2008,23(9):1585-1590.(in Chinese) [6] Erdem E,Kontis K,Albayrak K,et al.Numerical investigation of flowfield inside a conical rocket nozzle in the presence of transverse injection .AIAA 2008-359,2008. [7] 刘辉,邢玉明.激波诱导矢量喷管流场的数值模拟及试验[J].推进技术,2011,32(4):544-549. LIU Hui,XING Yuming.Computational and experimental analysis of the flow field in shock vector control nozzle[J].Journal of Propulsion Technology,2011,32(4):544-549.(in Chinese) [8] Najjar F M,Ferry J P,Haselbacher A,et al.Simulations of solid-propellant rockets:effects of aluminum droplet size distribution[J].Journal of Spacecraft and Rockets,2006,43(6):1258-1270. [9] Ragini A,Kenneth K K.Numerical simulation of graphite nozzle erosion with parametric analysis .AIAA 2010-6848,2010. [10] 于勇,刘淑艳,张世军,等.固体火箭发动机喷管气固两相流动的数值模拟[J].航空动力学报,2009,24(4):931-937. YU Yong,LIU Shuyan,ZHANG Shijun,et al.Numerical simulation of gas-particle flow in nozzle of solid rocket motor[J].Journal of Aerospace Power,2009,24(4):931-937.(in Chinese) [11] Roe P L.Approximate riemann solvers,parameter vectors,and difference schemes[J].Journal of Computational Physic,1997,135(2):250-258. [12] Menter F R.Two equation eddy viscosity turbulence models for engineering applications[J].AIAA Journal,1994,32(8):1598-1605. [13] 周力行.湍流气粒两相流动和燃烧的理论与数值模拟[M].北京:清华大学出版社,1991. [14] 刘辉,邢玉明,额日其太.气体二次喷射矢量喷管三维流场计算[J].北京航空航天大学学报,2009,35(10):1174-1178. LIU Hui,XING Yuming,ERIQITAI.Computation of the three-dimensional flow field in secondary gas injection for thrust vectoring nozzle[J].Journal of Beijing University of Aeronautics and Astronautics,2009,35(10):1174-1178.(in Chinese) [15] Forder A,Thew M,Harrison D.A numerical investigation of solid particle erosion experienced within oilfield control valves[J].Wear,1998,216(2):184-193.
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