Study of Turbulent Flow of Film Cooling Holes with Lateral Expanded Exits

作     者：施红辉 佐佐俊祐 SHI Hong-hui;SASA Shunyuu

作者机构：Department of Mechanics Zhejiang University Hangzhou 310027 China LNM Institute of Mechanics Chinese Academy of Sciences Beijing 100080 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4期

页      面：200-207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）] 

主　　题：turbulent flow film cooling lateral expanded hole hot wire anemometry flow visualization 

摘      要：Hot wire measurements and flow visualization are presented for studying the turbulent flow field over a flat gas turbine film cooling blade with lateral expanded holes. Three mass flux ratios of jet to free stream, M = 0.5, 0.89, 1.5, are tested. The streamwise velocity, the turbulent intensities and the Reynolds shear stress are measured. The effect of the lateral expanded holes on the improvement of the turbulent flow field for film cooling of gas turbines can be analyzed from the measured spatial di...