旋转固体发动机燃烧室-喷管两相流数值仿真  

Numerical Simulation on Two-Phase Flow for Spinning Solid Rocket Motor Chamber-Nozzle

作　　者：冯喜平[1] 赵胜海[1] 曹琪[1] 

机构地区：[1]西北工业大学航天学院,陕西西安710072

出　　处：《计算机仿真》2011年第7期95-99,共5页Computer Simulation

摘　　要：针对旋转引起的固体发动机内弹道性能和热防护性能变化影响发动机推力性能,从旋转对发动机内部燃气流动影响出发,用Reynolds时均N-S方程、Reynolds应力方程湍流模型(RSM)和颗粒随机轨道模型,在FLUENT软件上对不同旋转转速的固体发动机燃烧室-喷管内气-固两相流动进行了一体化数值仿真,比较了有无旋转两种状态下的流场结构,研究了转速对流场结构和发动机热结构的影响,并进一步研究了发动机的工作特性。仿真结果表明,发动机旋转使燃烧室内部流场结构发生显著变化,流场结构呈组合涡形式,粒子严重偏离发动机对称轴,导致燃烧室压强升高,推进剂燃速增大,发动机工作时间变短,热防护环境恶化,工作性能降低。这些变化随转速的增加呈现加剧趋势。研究结果为发动机设计提供了一定的技术支持。Aiming at the problem that the changing interior ballistic trajectory performance and thermal protection performance of Solid Rocket Motor（SRM） caused by spinning influence the perfoamance of the motor thrust,based on the impact of spinning on SRM inner gas flow,with FLUENT software,N-S Equations,Reynolds Stress Model（RSM） and Particle Track Model,the gas-solid two-phase flow numerical simulation of SRM chamber-nozzle integration was done in different spinning speed conditions.The flow field features were compared and analyzed between spinning and non-spinning states.The spinning speed influences on flow field features and thermo-structure of motor were researched.Further,the SRM working characteristics were researched.The results show that spinning of SRM changes the chamber flow field features significantly,flow field features present combinatorial eddy,and it makes chamber pressure increasing,propellant burning rate increasing,motor working time decreasing,thermal protection conditions deteriorating,working performance descending since particle departs motor symmetry axis severely;and these changes enhance with spinning speed increasing.The research results would make certain technical support for motor design.

关 键 词：固体火箭发动机 旋转 两相流动 数值模拟 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]