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本文通过圆柱座标系径向瞬时热传导偏微分方程,对喷管硅基内衬扩张段进行了温度分布数值计算.喷管结构是以石墨为喉衬,高硅氧/酚醛为收敛段、扩张段内衬,并为喉部背衬;壳体是钢.计算中考虑材料烧蚀时形成炭化层、热解层、原始材料层等多层结构,以及烧蚀边界的退移和材料物性随温度的变化.通过座标变换,将移动边界问题转化为定边界问题,计算结果与实验结果吻合良好.
In this paper, the numerical calculation of the temperature distribution in the inner expansion of silicon-based liner is carried out through the radial differential thermal transient partial differential equation in the cylindrical coordinate system.The nozzle structure is based on graphite as throat lining, high silicon oxygen / Section lining, and laryngeal backing; the shell is steel. Considering the multi-layer structure of carbonized layer, pyrolytic layer and original material layer when material ablation is taken into account, the ablation and material property of ablation boundary The change of temperature is transformed into a fixed boundary problem by coordinate transformation. The calculated results are in good agreement with the experimental results.