径向开槽药柱发动机内流场数值模拟

采用时间相关的显示ＭａｃＣｏｒｍａｃｋ预估－校正两步格式和可压缩全Ｎａｖｉｅｒ－Ｓｔｏｋｅｓ方程，计算了轴对称径向开槽药柱发动机内流场。计算中采用了贴体坐标系统和Ｂａｌｄｗｉｎ－Ｌｏｍａｘ代数湍流模型。边界参数计算采用参考平面上的特征线法和物理边界条件。通过大量算例的分析表明，方法有效，计算结果合理。当有集中质量加入时，燃烧室头部压强升高，喷射强度和开槽口的倾斜方向对头部压强也有较大的影响。

A NUMERICAL SIMULATION OF INTERNAL FLOWFIELDS IN SOLID PROPELLANT ROCKET MOTOR WITH RADIALLY SLOTTED GRAIN

In this paper, MacCormack's time-dependent explicit scheme is used to solveaxisymmetric mienal flow fields of the solid propellant rocket motor. The governing equations arecompressible full Navier-Stokes equations. In the calculation, the Boundary-Fitted-Coordinate systemis applied to transform a physic plane into calculation plane, the governing equations in calculationplane are obtained. A kind of arc-hyperbolic-sine function is utilized to construct the partialconcentrated grids, so that the region in which the physical variables have greater gradient will havemore grids than elsewhere. A turbulent model based on the Baldwin-Lomax algebraic scheme isemployed toget the coefficient of turbulent viscosity. The parameters on boundary of flow field aredetermined by characteristic line method on a reference plane and physic boundary conditions. Thenumerical results indicate that the numerical method employed here is effective. When concentratedmass is injected into the chamber, the pressure at the chamber head raises, which also depends oninjection mass ratio and jet position and the outlet direction of slot.