航空学报 > 2004, Vol. 25 Issue (6): 551-555

吹风比对气膜冷却效率影响的实验研究

韩振兴1, 末永洁2, 刘石1   

  1. 1. 中国科学院工程热物理研究所 北京 100080;2. 三菱重工业株式会社高砂研究所 日本
  • 收稿日期:2003-11-04 修回日期:2004-03-18 出版日期:2004-12-25 发布日期:2004-12-25

Experimental Research on Film Cooling Effectivenesses at Different Blowing Ratios

HAN Zhen-xing1, Kiyoshi Suenaga2, LIU Shi1   

  1. 1. The Institute of Engineering Thermophysics CAS, Beijing 100080, China;2. Takasago Research and Development Center, MITSUBISHI Heavy Industries LTD, Japan
  • Received:2003-11-04 Revised:2004-03-18 Online:2004-12-25 Published:2004-12-25

摘要:

以叶片作为研究对象,在主流风速为40m/s,弦长雷诺数为74400条件下,应用红外成像技术作为测温手段,研究了不同吹风比对叶片吸力侧和压力侧的气膜冷却效率分布的影响。吸力侧实验在3个吹风比分别为0.5,1.0和1.5条件下进行。压力侧实验在4个吹风比下进行,分别为0.5,0.75,1.0和1.7。从实验结果来看,在压力侧吹风比1.0条件下的冷却效果最好;对于吸力侧吹风比0.5条件下的冷却效率为最佳。

关键词: 气膜冷却, 冷却效率, 红外成像, 压力面, 吸力面

Abstract:

The film cooling effectiveness distributions on one test blade are studied and the infrared thermography is adopted to measure the temperatures on the surface of the blade. The mainstream velocity is kept to be 40m/s, and the Renolds number based on the chord length of the blade is 74400. The experiments are done on the suction side at three different blowing ratios, 0.5,1.0 and 1.5; and those on the pressure side at four different blowing ratios, 0.5,0.75,1.0 and 1.7. According to the experiment results, the effectiveness of film cooling at blowing ratio 1.0 is the best, while the optimal on the pressure side is at blowing ratio 0.5.

Key words: film cooling, cooling effectiveness, infrared thermography, pressure side, suction side