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为了分析再生冷却式液体火箭发动机推力室内壁失效机理、判断失效位置及确定循环次数,对其进行流-热-固耦合计算。流-热耦合模拟推力室再生冷却耦合传热过程并为热-固耦合提供边界条件,热-固耦合对推力室壁在循环加载下的变形进行三维结构非线性分析。通过计算,得到了推力室壁在单循环各阶段和循环加载下的应力应变分布,对计算结果进行后处理,得到了推力室内壁失效时的循环次数。结果表明,推力室内壁在循环热和机械载荷作用下向推力室内鼓起和变薄,喉部上游冷却通道中心最先失效。
In order to analyze the failure mechanism of the thrust wall of regeneratively cooled liquid propellant rocket engine, determine the failure location and determine the number of cycles, and calculate the flow-heat-solid coupling. Flow-heat coupling simulates the heat transfer process of the thrust chamber through regenerative cooling and provides the boundary conditions for the thermo-mechanical coupling. The three-dimensional nonlinear structural analysis of the deformation of the thrust chamber wall under cyclic loading is performed by thermo-mechanical coupling. Through the calculation, the stress and strain distribution of the thrust chamber wall at each stage of single cycle and cyclic loading are obtained, and the calculation results are post-processed, and the number of cycles when the thrust chamber inner wall fails is obtained. The results show that the inner wall of the thrust chamber is bulged and thinned into the thrust chamber under cyclic heat and mechanical loads, and the center of the cooling channel upstream of the throat is the first to fail.