固体火箭发动机气动喉部的两相流数值模拟  

Simulation for the two-phase flow aerodynamic throat of solid rocket motors

作　　者：谢侃[1] 王一白[1] 刘宇[1] 

机构地区：[1]北京航空航天大学宇航学院,北京100191

出　　处：《推进技术》2010年第1期56-60,共5页Journal of Propulsion Technology

摘　　要：本文对两相流条件下的环缝式气动喉部方案进行了数值模拟。气-粒两相流动模型采用二维轴对称欧拉-拉格朗日模型。研究了二次流不同喷射位置、角度、流率及喷嘴个数对气动喉部调节有效喉部面积大小的影响规律。模拟得到了两相流条件下气动喉部的流场特征,结果表明使二次流的喷入位置越靠近喉部、增大二次流流量或减小喷射角度都能明显增加气动喉部调节性能;由此归纳出增强气动喉部对主流扼流能力的两种主要机制,即增加挤压和流阻。A ring aerodynamic throat concept in two-phase flow condition was simulated numerically. The gas-solid two-phase flow model adapted was two-dimensional axial Euler-Lagrange model. The influence and rules of secondary flow injection positions, injection angles, secondary flow rates and injector numbers to the modulation performance of aerodynamic throat were studied. The flow characters of aerodynamic throat in two-phase flow conditions were attained from simulation, and the results show that the performance of aerodynamic throat can be obviously increased by getting secondary flow injector close to throat, increasing secondary flow rate or decreasing secondary flow injection angle. Two main mechanism for aerodynamic throat to strengthen the ability of choking flow, which were increasing extrusion and flow drag, were summarized from the simulation results.

关 键 词：固体推进剂火箭发动机 气动喉部^+ 二次流 两相流^+ 数值仿真 

分 类 号：V435.11[航空宇航科学与技术—航空宇航推进理论与工程]