摘要
对航空发动机的一种先进冷却方式,冲击/发散复合冷却方式的发散壁燃气侧换热系数进行了试验研究。考虑了影响燃气侧换热系数的流动和几何参数,它们是主流雷诺数、吹风比以及几何结构。采用比较法研究燃气侧换热系数,基准换热系数与经典传热准则计算值相比,精度在±7%以内。研究发现主流是充分发展湍流时,主流雷诺数对发散壁燃气侧换热系数基本无影响,而吹风比和几何结构是主要的影响因素。多排气膜叠加,也使得换热增强系数沿流向增加。对实验结果总结了经验关系式,可以用于该种冷却结构的传热设计和校验。
This paper presented the experimental study of effusion wall film heat transfer coefficients for impingement/effusion double wall cooling method, which was one of the advanced cooling methods of combustor or liner in aeroengine. The investigation focused on the factors affecting the heat transfer coefficients, which were main flow Reynolds number, blowing ratio and configurations. The heat transfer coefficients were studied using the comparing method, and the basic heat transfer coefficients were compared with classical heat transfer result, showing that the difference was within ±7%. The experimental results show that the main flow Reynolds number has no effect on the effusion wall film heat transfer coefficient, while the blowing ratio and configurations are the main factors. The more the rows of cooling film, the higher the heat transfer coefficient along the flowing direction. The experimental results were correlated, and the correlation could be used in the heat transfer design and validation of cooling schemes.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2004年第2期213-218,共6页
Journal of Aerospace Power
基金
国防科技重点实验室基金资助项目(98JS48.3.1.HK5401)
关键词
航空发动机
对流换热系数
冲击冷却
发散冷却
燃烧室
Aerospace engineering
Combustors
Cooling
Correlation methods
Propulsion
Reynolds number
