可重复使用火箭发动机再生冷却槽失效分析

完成了可重复使用液体火箭发动机推力室再生冷却槽热力循环载荷下的蠕变非弹性热结构分析,对比研究了各向同性硬化和随动硬化定律对冷却槽结构分析的影响,并在多循环结构场基础上分析了冷却槽"狗窝"失效过程.结果表明可以通过选取热传导率差别小的内外壁材料、优化几何结构改善温度场及结构场;各向同性和随动硬化结构曲线变化趋势相似,但塑性应变有较大差别,残余应变相差约0.06%;多循环加载中每个循环的结构曲线形状相似并不断右移,硬化效应明显,低周疲劳损伤和蠕变损伤分别取决于循环载荷下的应变和应力值.

Failure analysis of reusable rocket engine coolant passage

Through the creep nonlinear thermal-structure analysis of the reusable combustion chamber coolant passage under cyclic thermal and mechanical loading, comparison between kinematic and isotropic hardening results was made to study the hardening influence. Basing on those cyclic structure results, the "dog house" failure model of coolant passage was implemented. Results indicate that the thermal and structure environment could be improved by introducing materials with similar thermal conductivity for the jacket and inner wall and optimizing the geometric model; the kinematic and isotropic hardening results were similar in illustrating the development of stress and strain under cyclic loadings, whereas at the remaining strain variance of approximate 0.06%; the strain hardening effect was obvious in those cyclic loops which was analogous each cycle and right moved, and the fatigue damage and creep damage were determined respectively by cyclic strain and stress.