液体火箭发动机推力室可重复使用技术

Reusable technology for liquid rocket engine thrust chamber

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.

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 in- ner wall material, closeout thickness and regenerative cooling channel aspect ratio on the us- able life of thrust chamber inner wall. Through computation, the stress and strain distribu- tion of thrust chamber wall at different stage of each cycle under different inner wall materi- als, closeout thicknesses and cooling channel aspect ratios were obtained, and a post pro- cessing method was applied to predict the damage of the thrust chamber inner wall. The re- suits 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.