液体火箭发动机推力室钎焊过程热固耦合分析
Thermal-mechanical coupling analysis on brazing of thrust chamber of liquid rocket engine
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摘要: 在考虑热电偶对真空炉加热分区电功率闭环控制的基础上,建立了液体火箭发动机推力室钎焊过程仿真计算的有限元模型.基于热固弱耦合方法,对推力室钎焊过程中的瞬态温度场和应力-应变分布进行了分析.确定了推力室在钎焊过程中热电偶所测温度与室壁温度的温差范围,得出了室壁温度的分布规律.应力-应变分布表明喉部内壁在焊接过程中易出现受压失稳.分析结论为改进钎焊工艺方案及探究室壁褶皱形成的深层次原因提供了理论基础.提出了工艺改进方案,并通过了试验验证,结果显示钎焊过程中推力室的褶皱现象得到有效控制.Abstract: The finite element model for the brazing of the thrust chamber has been established based on the closed-loop control of electric power in heater band of vacuum furnace. After analyzing the transient temperature field and the strain-stress distribution of thrust chamber through the weak thermal-mechanical coupled method, the temperature difference between the thermocouple and the chamber wall is determined, and the temperature distribution of the chamber wall is also obtained. The strainstress shows that the buckling of the pressed inner wall nearby the throat is easily generated during brazing. The results will lay a theoretical foundation for improving the brazing procedure and exploring the failure mechanism of thrust chamber wall. The improved brazing procedures are put forward and verified by brazing test.