摘要
某型发动机的实际涡轮盘腔冷却结构被简化成外缘预旋进气的旋转空腔模型，以实验方法研究了旋转雷诺数（Ｒｅω）、冷气雷诺数（Ｒｅｚ）、哥拉晓夫数（Ｇｒ＊）对主盘局部换热及流阻特性的影响。实验发现，冷气雷诺数、旋转雷诺数的增大，使主盘局部换热系数在盘缘附近迅速增大，而在接近盘心时出现负值；阻力系数随旋转雷诺数的增大而减小，随冷气雷诺数的增大而增大。
A turbine cooling configuration of aero engine was simplified to be the rotating cavity with an tangential pre swirling fringe guide van and a radial outlet. The influences of rotating Reynolds number, cooling air Reynolds number and Grashoff number on the local heat transfer and flow characteristics were experimentally investigated. Experiment indicate that the flow pattern in the rotating cavity is mainly controlled by Rossby number. The local heat transfer coefficient on the edge of main disk rapidly increases with the increase of cooling air Reynolds number and rotating Reynolds number. The local heat transfer coefficient becomes negative near the center of the disk. The flow friction coefficient increases with the increase of cooling air Reynolds number and decreases with the rotating Reynolds number
出处
《推进技术》
EI
CAS
CSCD
北大核心
1998年第6期45-49,共5页
Journal of Propulsion Technology
