Numerical studies on four-engine rocket exhaust plume impinging on flame deflectors with afterburning  

作　　者：Zhi-tan Zhou Chang-fang Zhao Chen-yu Lu Gui-gao Le 

机构地区：[1]School of Mechanical Engineering,Nanjing University of Science and Technology,Nanjing,210094,China

出　　处：《Defence Technology（防务技术）》2021年第4期1207-1216,共10页Defence Technology

摘　　要：This paper studies the four-engine liquid rocket flow field during the launching phase.Using threedimensional compressible Navier-Stokes equations and two-equation realizable k-epsilon turbulence model,an impact model is established and flow fields of plume impinging on the two different shapes of flame deflectors,including wedge-shaped flame deflector and cone-shaped flame deflector,are calculated.The finite-rate chemical kinetics is used to track chemical reactions.The simulation results show that afterburning mainly occurs in the mixed layer.And the region of peak pressure occurs directly under the rocket nozzle,which is the result of the direct impact of exhaust plume.Compared with the wedgeshaped flame deflector,the cone-shaped flame deflector has great performance on guiding exhaust gas.The wedge-shaped and cone-shaped flame deflectors guide the supersonic exhaust plume away from the impingement point with two directions and circumferential direction,respectively.The maximum pressure and temperature on the wedge-shaped flame deflector surface are 37.2%and 9.9%higher than those for the cone-shaped flame deflector.The results provide engineering guidance and theoretical significance for design in flame deflector of the launch platforms.

关 键 词：Four-engine rocket AFTERBURNING Impinging flow field Different deflectors Numerical simulations 

分 类 号：TJ7[兵器科学与技术—武器系统与运用工程] V553[航空宇航科学与技术—人机与环境工程]