摘要
为研究涡轮叶片复合冷却传热特性,建立了涡轮叶片复合冷却实验测试平台,对叶片前缘区域进行了射流冲击+气膜冷却实验测试,详细研究了冷气吹风比M、前缘位置、主流雷诺数Re以及温度比Tg/Tc对冷却效率的影响规律。实验结果表明,冷却效率随吹风比的增大而增大,随Tg/Tc的增大而减小。本文实验条件下,最佳吹风比约为1.0;越靠近前缘驻点,冷却效率越大;主流雷诺数对冷却效率的影响不大,但总体上仍表现出雷诺数越大,冷却效率越高。
In order to study the heat transfer characteristics of turbine blades, this article presents an experimental study of composite cooling of impingement and film on the leading edge of a turbine blade. The effect of factors on cooling effectiveness, such as blowing ratio, position of leading edge, main flow Reynolds number and comparison of temperature Tg/Tc, is investigated in detail. The experimental results show that cooling effectiveness improves with the increase of blowing ratio and deteriorates with the increase of Tg/Tc. Under the conditions used in this article, the optimal blowing ratio is about 1.0. The closer the cooling is to the stagnant point, the higher is its effectiveness. The Reynolds number of the main flow has a relatively small effect on cooling effectiveness, but the cooling effectiveness still increases with increasing Reynolds number as a whole.
出处
《航空学报》
EI
CAS
CSCD
北大核心
2009年第9期1618-1623,共6页
Acta Aeronautica et Astronautica Sinica
基金
国家自然科学基金(50776087)
关键词
涡轮叶片
复合冷却
实验
冷却效率
吹风比
turbine blade
composite cooling
experiment
cooling effectiveness
blowing ratio
