Effect of Diffusively Shaped Holes on the Turbulent Flow Field of a Film Cooling Plate

作     者：施红辉 桐山贤司 伊藤基之 SHI Hong-hui;Kenji Kiriyama;Motoyuki Itoh

作者机构：Department of Mechanics Zhejiang University Hangzhou 310027 China Department of Mechanical Engineering Nagoya Institute of Technology Nagoya 466-8555 Japan 

出 版 物：《Chinese Journal of Aeronautics》 (中国航空学报（英文版）)

年 卷 期：2002年第15卷第1期

页      面：6-11页

核心收录：

学科分类：082502[工学-航空宇航推进理论与工程] 08[工学] 0802[工学-机械工程] 0825[工学-航空宇航科学与技术] 0801[工学-力学（可授工学、理学学位）] 

基　　金：T his work was supported by the Nagoya Insti tute of Technology under a project of Study of 3 Dimensional Turbulent Boundary Layer on Gas T urbine Blades during 1996 2000. Mr. K. Kawai and Mr. Y. Sasaare thanked for their help in the experiment. Dr. T. Yoshida of the National Aerospace Laboratory  Tokyo  is thanked for his kind discussion 

主　　题：turbulent boundary layer film cooling diffusion hole hot wireanemometry 

摘      要：The gas turbine blades with diffusion film cooling holes are newlydeveloped blade struc- tures in the hydrogen combustion gas turbine,which has an extremely high inlet gas temperature (1700 deg. C). TheFluid Machinery Laboratory of Nagoya Institute o Technology conductedfirstly a new research o the turbulent flow field over the gasturbine blade with diffusion film cooling holes in Japan. Normal-typeand X-ray hot wires were applied in the measurement of the flowfield.