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选取内、外调节片和隔热屏建立几何模型,基于封闭腔净辐射模型和壁面热平衡模型建立了燃气辐射与喷管壁面温度的耦合算法.波段为1~5μm的气体辐射采用窄波带模型计算,其他波段不考虑气体辐射,建立辐射净热流密度-有效辐射亮度-壁面温度的关联式求解燃气与壁面的辐射换热,采用牛顿-拉斐尔森迭代法求解壁面热平衡方程计算其温度.对某轴对称矢量喷管(偏转20°),计算了喷管壁面的红外光谱辐射和辐射净热流密度,以及各部分结构的温度.作为验证,还计算了文献中某液体火箭发动机轴对称矢量喷管壁面的辐射净热流密度,与文献的结果进行对比一致性较好.研究表明:轴对称矢量喷管偏转段沿周向的辐射热流密度和温度差异很大,沿偏转方向部位壁面的温度和辐射热流密度都较低,偏转方向壁面的温度比相反方向大约低10%,辐射热流密度大约低50%.
Based on the model of the closed cavity net radiation and the wall thermal equilibrium model, the coupling algorithm between the gas radiation and the wall temperature of the nozzle was established. The gas band of 1 ~ 5 μm was irradiated by a narrow band model The radiation of heat transfer between the gas and the wall surface was calculated by using the correlation of the net radiant heat flux density - the effective radiation brightness - the wall temperature. The Newton-Raphson iteration method was used to solve the wall heat balance equation to calculate the temperature. For an axisymmetric vector nozzle (deflected by 20 °), the infrared spectrum radiation and net heat flux density of the nozzle wall and the temperature of each part of the structure were calculated. As an example, the axial symmetry vector of a liquid rocket motor The radiative net heat flux density of the nozzle wall is in good agreement with the results of the literature.The results show that there is a great difference between the radiant heat flux density and the temperature along the circumferential direction of the deflection segment of the axisymmetric vector nozzle, And radiant heat flux density are both lower, the deflection wall temperature is about 10% lower than the opposite direction, and radiant heat flux density is about 50% lower.