双斜喷管固体火箭发动机流动特性数值模拟

Numerical simulation on flow field of double-nozzle solid rocket motors

应用计算流体力学软件PHOENICS从二维湍流N S方程出发 ,对有 /无斜切的双喷管固体火箭发动机内流场进行了数值模拟。研究表明 ,对无斜切模型的喷管偏转角从 15°变化到 3 0° ,轴向推力损失约达 10 %。有斜切模型的喷管形状不对称 ,内流在出口处产生的扰动在较长一侧喷管壁反射 ,出现激波现象 ,引起流动的变化。

Inner flow field of solid rocket motor (SRM) with/without double nozzle with sloped exit is simulated numerically based on N S equations with k ε turbulent model.When the angle of nozzle is changed from 15° to 30°,the thrust of SRM decreases by 10%.Because nozzle shape with oblique cut models is asymmetric,the disturbance produced at the exit of nozzle is reflected on the longer side and causes shock waves in the inner flow.