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以不可压ＮＳ方程为基础，在旋转相对坐标系中，采用贴体坐标和ＳＩＭＰＬＥ法，对给定结构的旋转固体火箭发动机燃烧室试车中气固两相湍流流动进行了数值模拟。不同时刻燃烧情况的计算结果表明：旋转对固体火箭发动机燃烧室燃气流动结构的影响随着燃烧肉厚的退移而显著增强；在发动机药柱的前翼燃烧消失后，前封头开口区域的气固两相切向涡开始变得强烈；切向涡的分布呈现Ｒａｎｋｉｎｅ 涡的特点，在发动机前开口区域涡的固核半径极小，旋转角速度极大，将会影响该区域的热防护，这也是导致固体火箭发动机地面旋转热试车前开口烧穿的重要原因之一。
Based on incompressible Navier-Stokes equations, the gas-solid two-phase turbulent flow in a rotating solid rocket engine combustion chamber for a given structure was numerically simulated using the body-fitted coordinate and the SIMPLE method in a rotating relative coordinate system. The calculation results of combustion at different times show that the influence of rotation on the gas flow structure of the solid rocket motor combustion chamber increases significantly with the retreat of flesh thickness. After the combustion of the front wing of the engine cylinder disappears, The gas-solid two-phase tangential vortex begins to become intense. The distribution of tangential vortex is characterized by Rankine vortex. The radius of solid nucleation in the front opening of the engine is extremely small, and the rotational angular velocity is extremely high, which will affect the thermal protection in this area , Which is also one of the important reasons leading to the burn-through of the opening of the solid rocket engine before the test run.