摘要
本文使用由半圆柱前缘和平直尾部组成的钝物体来模拟涡轮叶片前缘,利用高温风洞实验测试平台,对前缘区域进行了内部射流冲击＋外部气膜冷却的实验研究,通过红外热像仪测量了叶片表面的温度场分布,分析了气膜吹风比、前缘位置、主流雷诺数对冷却效率的影响规律。实验中吹风比的变化范围为0.24~1.67,主流雷诺数的变化范围为55 420~111 615。实验结果表明：冷却效率随吹风比的增大而增大,在本文实验参数范围内,最佳吹风比约为0.81;位置2处的冷却效率最高;随着主流雷诺数的增大冷却效率有所提高。
This paper presents an experimental study of composite cooling of internal impingement and external film on the leading edge of a simulated turbine blade in wind tunnel. The surface temperature distribution of blade was obtained by infrared photographer. Adiabatic cooling effectiveness was calculated from the wall temperature,the main flow and coolant temperatures for various coolant blowing ratio and main flow Reynolds numbers. In the experiment,coolant blowing ratio varied from 0. 24 to 1. 67,and main flow Reynolds number from 55 420 to 111 615. Results show that the cooling effectiveness increases with increased film blowing ratio. The best blowing ratio is about 0. 81. The performance of the cooling effectiveness is improved with increased mainstream Reynolds.
出处
《燃气轮机技术》
2016年第2期8-14,共7页
Gas Turbine Technology
基金
国家自然科学基金资助项目(51276116)
关键词
涡轮叶片
复合冷却
红外热像仪
吹风比
冷却效率
turbine blade
composite cooling
infrared radiation camera
blowing ratio
cooling effectiveness
