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本文根据固体火箭发动机喷管沉积现象的实验结果,提出一种简化的沉积传热模型-两区域有限平壁,移动的相变边界,变壁温对流换热边界条件下的一维瞬态导热,并应用热平衡积分法求解了这种模型. 热平衡积分法本质上类似于卡门一波尔豪森求解边界层问题的动量和能量积分法.利用这种方法,本文获得了沉积情况下喉衬和沉积层内的温度分布函数,和各边界面的温度响应函数,并给出了计算实例.本文还导出了几个反映沉积因素的无因次数组,据此讨论了减薄喷管喉衬厚度对控制沉积的作用.本文为分析喷管沉积机理提供了一些理论依据.
Based on the experimental results of the deposition of solid rocket motor nozzles, a simplified model of deposition heat transfer is proposed, which is the finite flat wall and the moving phase boundary of the two regions. One-dimensional transient thermal conduction under variable wall temperature convective heat transfer boundary conditions , And the thermal equilibrium integral method is used to solve this model.The thermal equilibrium integral method is similar in nature to the momentum and energy integral method of Carmen-Bolhausen for solving the boundary layer problem.Using this method, The temperature distribution function in the sediment layer and the temperature response function of each boundary are given and the calculation example is also given.In this paper, several dimensionless arrays reflecting deposition factors are also deduced, On the control of the deposition of the role.This paper for the analysis of nozzle deposition mechanism provides some theoretical basis.