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为了研究大型分段装药发动机绝热环限燃层的烧蚀规律和特性,针对典型发动机开展了不同时刻和限燃层高度条件下三维两相流场的数值模拟,进行了限燃层表面烧蚀环境的特征分析和烧蚀状态参数提取,设计并研制了地面模拟烧蚀实验装置,开展了不同颗粒冲刷状态条件对限燃层烧蚀影响规律的实验研究,并采用扫描电镜分析了限燃层迎风面和背壁面炭化层的微观形貌。研究结果表明:(1)大型分段装药发动机流道中不同位置处绝热环限燃层表面的两相流冲刷状态不同,由于绝热环在流道中的阻碍作用,其表面形成了一种颗粒聚集浓度较低、冲刷速度较高而气相速度较低的烧蚀环境;(2)地面模拟实验结果表明绝热环限燃层的炭化烧蚀率随颗粒冲刷速度增加而增加,且增加幅度逐渐变大;(3)实验后限燃层的核心冲刷区域表面无炭化层残留,其烧蚀模式由机械剥蚀破坏效应主导。
In order to study the ablation laws and characteristics of the flame-retardant layer on the adiabatic ring of large-scale segmented charge engine, the numerical simulation of the three-dimensional two-phase flow field at different time and confinement height was carried out for a typical engine. The characteristics of erosion environment and the extraction of ablation state parameters, a ground simulated ablation experimental apparatus was designed and developed, and the influence of different particle erosion conditions on the ablation of the flame-retardant layer was studied. The effects of flame-retardation The micro-topography of the windward and back wall carbonized layers. The results show that: (1) Two-phase flow erosion on the flame-retardant surface of the adiabatic ring at different positions in the large-scale segmented charge passage is different. Due to the obstruction of the adiabatic ring in the flow passage, a particle agglomeration is formed on the surface Low concentration, high erosion rate and low gas velocity. (2) The simulation results show that the carbonization ablation rate of the flame-retardant layer with adiabatic ring increases with the increase of particle erosion rate, and the increase rate becomes larger ; (3) No carbonized layer remained on the core scouring area of the limited combustion layer after the experiment, and its ablation pattern was dominated by mechanical erosion and destructive effect.