发动机内流场湍流数值模拟

Numerical Simulation of Turbulent Internal Flowfield in Solid Rocket Motor

以可压缩的全Ｎ－Ｓ方程为控制方程，用显式有限差分格式对燃烧室－－喷管轴对称湍流内流场进行了数值模拟。计算中采用ＭａｃＣｏｒｍａｃｋ两步显格式和Ｂａｌｄｗｉｎ－Ｌｏｍａｘ代数湍流模型，得到了管状装药发动机内流场的数值解，取得了令人满意的结果。此方法对发动机的设计有实际的工程参考价值。

The governing equations are the compressible full Navier-stokes equations. Maccormack's time-dependent explicit scheme is used to solve axisynmetric internal flowfield of the solid propellant rocket motor. A turbulent model based on the Bald win-lomax algebraic scheme is employed to get the coefficient of turbulent viscosity. The solution of the internal flowfield for the soliel rocket motor with tube grain is obtained.The results are satisfactory. The methods are of reference value to the engineering design of SRM.