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ACTA AERONAUTICAET ASTRONAUTICA SINICA ›› 2004, Vol. 25 ›› Issue (6): 551-555.

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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

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