发动机喷管内流场对流换热系数影响因素的数值分析  

Numerical analysis of influence factor on convective heat transfer coefficient about nozzle internal flow

作　　者：王明华[1] 陈劲松[1] 

机构地区：[1]北京航天发射技术研究所,北京100076

出　　处：《火箭推进》2011年第3期32-37,共6页Journal of Rocket Propulsion

摘　　要：基于Roe-FDS格式,采用标准k-ε湍流模型对某液氧煤油发动机喷管内部燃气流对喷管内壁的对流传热换热系数进行了数值仿真与研究,分析了网格雷诺数以及恒温壁壁温对喷管内壁对流换热系数的影响。当近壁面网格第一层法向高度为10-3 mm数量级时,仿真结果与工程估算公式的计算结果相吻合。同时,在一定范围内,对流换热系数随来流速度的增大而增大,恒温壁的壁温对对流换热系数的影响则较小。The convective heat transfer coefficient of nozzle internal flow in a liquid oxygen-kerosene rocket engine is simulated with Roe-FDS computation format and a standard k-ε turbulence model.The effects of mesh Reynolds number and constant wall temperature on the convective heat transfer of nozzle internal flow are analyzed.The simulated result is in good agreement with the result of engineering estimation when the order of magnitude of first near-wall mesh altitude is 10-3 mm.In a given scope,the convective heat transfer coefficient increases with the increase of flow velocity,and the influence of constant wall temperature on the convective heat transfer coefficient is indistinctive.

关 键 词：喷管对流换热系数 网格雷诺数 恒温壁 边界层 气动热 

分 类 号：V434-34[航空宇航科学与技术—航空宇航推进理论与工程]