液体火箭发动机推力室可重复使用技术

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.

Reusable technology for liquid rocket engine thrust chamber

To validate the reusable technology for liquid rocket engine thrust chamber,the fluid-structural coupling method was adopted to simulate the effect of thrust chamber inner wall material,closeout thickness and regenerative cooling channel aspect ratio on the usable life of thrust chamber inner wall.Through computation,the stress and strain distribution of thrust chamber wall at different stage of each cycle under different inner wall materials,closeout thicknesses and cooling channel aspect ratios were obtained,and a post processing method was applied to predict the damage of the thrust chamber inner wall.The results show that the use of high yield strength inner wall material with reasonable ductility,low-stiffness closeout and high aspect ratio cooling channel can decrease the damage of thrust chamber inner wall and extend the usable life the thrust chamber.