固体火箭发动机含径向缺陷喷管数值仿真分析  

Numerical simulation and analysis of nozzle with radial defect in solid rocket motor

作　　者：武越 刘洋 倪铮[1] 王尚春 WU Yue;LIU Yang;NI Zheng;WANG Shangchun(Shaanxi Province Aeronautics and Astronautics Propulsion Research Institute,Xi'an 710003,China;Science and Technology on Combustion,Internal Flow and Thermo-Structure Laboratory,Northwestern Polytechnical University,Xi'an 710072,China)

机构地区：[1]陕西空天动力研究院有限公司,陕西西安710003 [2]西北工业大学燃烧、热结构与内流场重点实验室,陕西西安710072

出　　处：《火箭推进》2022年第4期21-28,共8页Journal of Rocket Propulsion

基　　金：国家自然科学基金(51876177)。

摘　　要：火箭发动机喷管的工作环境极为恶劣,固体火箭发动机在热试状态下经常会出现因喷管喉衬加工过程中的工艺缺陷导致的开裂失效事故。针对某型固体火箭发动机试车后喷管喉衬断裂现象,基于真实裂纹形貌进行建模,并开展发动机典型工作时刻下的三维两相数值模拟,旨在获得喷管喉衬不同断裂间隙内流场温度、压强、热流密度与速度场分布及对比情况。研究结果表明:喷管喉衬断裂间隙中温度远高于喷管内流场中的温度,间隙较大处压强高于间隙较小处,燃气进入断裂间隙后速度迅速降低,且在间隙中形成多处回流,凝相粒子主要集中在中央流道,没有凝相粒子进入断裂间隙,靠近喷管壁面断裂根部热流密度最高。The working environment of rocket engine nozzle is extremely harsh.Under the hot fire test of solid rocket motor,the cracking and failure accidents often occur due to the technological defects of the nozzle insert.In this paper,aiming at the fracture phenomenon of the nozzle throat insert after the test of a certain solid rocket engine,the model was built based on the real crack morphology,and three-dimensional two-phase numerical simulation was carried out under the typical working time of the engine.The purpose was to obtain the distribution and comparison of the temperature,pressure,heat flux and velocity field in different fracture gaps of the nozzle throat insert.The research results show that the temperature in the nozzle throat insert fracture gap is much higher than the temperature in the flow field inside the nozzle,and the pressure in the larger gap is higher than that in the smaller gap.After the gas enters the fracture gap,its speed decreases rapidly and multiple backflows are formed in the gap.The condensed-phase particles are mainly concentrated in the central flow channel and no condensed phase particles enter into the fracture gap,and the heat flux is the highest near the fracture root of the nozzle wall.

关 键 词：固体火箭发动机 喷管 缺陷 三维两相流动 数值模拟 

分 类 号：V435.14[航空宇航科学与技术—航空宇航推进理论与工程]