摘要
喷管是各种喷气或反作用发动机的重要部件 ,发动机通过高温和高压燃气由喷管向后喷出而获得向前的推力 ,燃气以对流和辐射的方式向喷管壁面放热 ,导致喷管温度急剧上升 ,为此采取等离子喷涂陶瓷涂层隔热防护 ,实际连续测量喷管壁温几乎是不可能的 ,因此通过模拟计算预示喷管工作过程中的壁温分布是非常重要的。本文根据高温发动机喷管的受热特点 ,对喷管内壁设计了 6种热喷涂涂层 ,利用Marc软件及Mentat前后处理程序 ,建立了轴对称喷管的物理模型 ,仿真计算了在不同涂层下喷管受固定温度热载时的温度场 ,分析了受热最严重的喉截面瞬态受热温度分布 ,为合理选择喷管基材及涂层材料。
Nozzles are very important parts of jet engines. Engines get their forward thrust from the nozzles by high temperature and high-pressure jets. Nozzle temperature increases rapidly resulting from the high temperature fuel jet through thermal conduction and radiation. Ceramic barrier coatings are therefore employed to protect the nozzle by plasma spray. It is impossible to measure the inner and outer surface temperature of a nozzle continuously. Yet it is very important to predict the temperature distribution along the cross-section of a nozzle by simulation and calculation. In view of the characteristics of a nozzle in high temperature engines enduring hot gas, six thermal barrier coatings are designed for the inner surface of nozzle. Physical model of the nozzle with axial symmetry is set up. With FEM method, Marc software and Mentat processing program, the temperature field of the nozzle with different coatings when exposed to fixed temperature load is simulated and calculated. The temperature distribution under instantaneous states along the cross-section of throat in the nozzle is analyzed where hot load is the most heavy. Thus it provides a scientific method for selecting materials of the substrate and coatings, as well as for optimizing the coatings.
出处
《兵工学报》
EI
CAS
CSCD
北大核心
2002年第2期209-211,共3页
Acta Armamentarii
