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为了验证液体火箭发动机推力室可重复使用技术,采用流-固耦合方法对推力室内壁材料、外壁厚度、冷却通道高宽比等影响推力室内壁寿命的因素进行了数值模拟.通过计算,得到了推力室内壁在不同内壁材料、不同外套厚度、不同冷却通道高宽比下单循环各阶段的应力、应变分布,对计算结果进行后处理,得到了内壁损伤.结果表明,采用高强度及延展性内壁材料、低刚性外套、大冷却通道高宽比可以减小推力室内壁损伤,延长推力室内壁使用寿命.
In order to verify the reusable technology of the liquid rocket engine thrust chamber, the factors that affect the life of the thrust chamber wall are numerically simulated by using the fluid-solid coupling method, including the material of the thrust chamber, the thickness of the outer wall and the aspect ratio of the cooling passage. The stress and strain distributions of the inner wall of the thrust chamber in different stages of single cycle under different inner wall materials, different jacket thicknesses and aspect ratios of different cooling channels were dealt with, and the damage of the inner wall was obtained. The results show that the high strength and ductility Wall material, low rigidity jacket, large cooling channel aspect ratio can reduce the thrust chamber wall damage, prolong the service life of the thrust chamber wall.