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绝热衬套
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The deposit phenomena of the nozzle throat happens sometimes in the operation of a rocket engine with the aluminized solid propellant. It can seriously affect the performance of the engine. This paper developed the heat transfer model of the throat deposit process according to the related experimental phenomena. It is assumed that the structure of the nozzle throat is composed of deposit layer, erosion protection throat liner,adiabatic liner and shell, and they have different heat transfer property.The thickness...

The deposit phenomena of the nozzle throat happens sometimes in the operation of a rocket engine with the aluminized solid propellant. It can seriously affect the performance of the engine. This paper developed the heat transfer model of the throat deposit process according to the related experimental phenomena. It is assumed that the structure of the nozzle throat is composed of deposit layer, erosion protection throat liner,adiabatic liner and shell, and they have different heat transfer property.The thickness of the deposit layer varies with time. Hence this is a non-steady heat transfer problem with a multilayer wall and variable boundary. On this heat transfer model the differential equations were based, and the finite difference complete concealed grids were used in the numerical analysis computation. The calculation results gave the temperature profile of the throat section and its variation law,and predicted the influences of the related factors on the throat deposition. The analysis results well accord with the experimental phenomena.

含铝推进剂的固体火箭发动机在工作过程中有时会发生喷管喉部沉积现象,可能对发动机性能带来严重的影响.本文根据有关实验现象,建立了喉部沉积过程的传热模型.假设喷管喉部结构由沉积层、耐熔喉衬、绝热衬套及外壳等导热性能不同的材料组成,其中沉积层的厚度是随时间变化的,是多层壁变边界的不稳定传热问题.根据喉部沉积的传热模型建立了偏微分方程组,采用有限差分完全隐式格式进行数值分析计算.计算分析结果给出了喉部截面温度场及其变化规律,并从理论上予示有关因素对喉部沉积的影响,与实验规律一致.

 
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