轴对称矢量喷管三维传热计算研究  

A Numerical Investigation of 3D Heat Transfer for Axisymmetric Vectoring Exhaust Nozzle

作　　者：金捷[1] 廖华琳[1] 朱谷君[2] 张晓英 

机构地区：[1]中国燃气涡轮研究院,成都610500 [2]北京航空航天大学,北京100083

出　　处：《燃气涡轮试验与研究》2002年第2期4-7,46,共5页Gas Turbine Experiment and Research

摘　　要：采用封闭腔理论算法 ,利用矢量喷管的三维内流场数值计算结果 ,对轴对称矢量喷管的壁温分布进行了数值计算。计算结果表明 ,在非矢量状态 ,喷管同一轴向位置处的周向壁温基本相同 ,壁温分布可按一维处理。在矢量状态 ,喷管同一轴向位置处的周向壁温相对差值达 15 % ,壁温分布呈现复杂的形式 ,必须采用三维计算方法计算壁温分布 ;喷管扩张段壁温明显高于非矢量状态。所开发的计算方法和程序既可用于轴对称矢量喷管的工程设计 ,也可为试验验证提供理论依据。Wall temperature distribution for axisymmetric vectoring exhaust nozzle(AVEN) has been computed by means of closure cavity theoretic algorithm and numerical computation of internal 3D flow field in AVEN. The computation reveals wall temperature distribution can be treated as 1D at non vectoring condition, since circumferential wall temperatures of one axis are essentially the same. At vectoring condition, circumferential wall temperature difference of one axis is greater than 15%. The distribution is very complicated, making it necessary for the wall temperature to be estimated by 3D method. Wall temperature at divergent section is significantly greater than at non vectoring condition. This computation method and code can be applied to engineering design of AVEN and used as theoretical foundation for test verification.

关 键 词：轴对称矢量喷管 传热 数值计算 壁温 

分 类 号：V231.1[航空宇航科学与技术—航空宇航推进理论与工程]