潜入式摆动喷管两相内流场数值模拟

Numerical simulation on two-phase inner flow field of submerged vectored nozzle

气相采用三维薄层近似N S方程,固相采用拉格朗日坐标系下颗粒轨道模型,计算方法采用显式ENO差分格式和分区多块网格技术,建立了固体火箭发动机内流场模拟软件。对轴对称JPL喷管进行模拟,计算结果与文献进行比较,符合较好。推广到实际三维装药型面时,发现颗粒数目增加导致计算效率降低。采用软件中的气相计算模块对潜入式摆动喷管内流场进行数值模拟,比较了喷管摆动角在发动机喉道附近引起流动变化,研究了非对称流动对喷管内表面压强的影响。

A numerical simulation of the flow in solid rocket motor, by using the Navier-Stokes equations in gas phase solution and a Lagrangian model in solid phase solution is presented. The code of CFD is based on a multiblock, structured grid, finite difference approach with explicit ENO scheme. The number of particle needed in 3-dimension calculation is so big that the application of the code is limited. The inner flow field of the solid rocket motor with submerged vectored nozzle is simulated with gas phase module of the code, and the influence of asymmetric flow on the pressure on nozzle wall is studied.