Measured overall effusion cooling effectiveness over a wide blowing ratio range using infrared imaging

作     者：ZHANG Chi SONG Bo LIN Yu-zhen XU Quan-hong LIU Yan 

作者机构：National Key Laboratory of Science and Technology on Aero-Engines School of Jet Propulsion Beijing University of Aeronautics and Astronautics Beijing 100191 China Jiangsu Chinfan Compressor Incorporation Changshu Economic Development Zone Jiangsu 215513 China China North Vehicle Research Institute China North Industries Group Corporation Beijing 100072 China 

出 版 物：《航空动力学报》 (Journal of Aerospace Power)

年 卷 期：2010年第25卷第7期

页      面：1454-1463页

核心收录：

学科分类：080704[工学-流体机械及工程] 08[工学] 0807[工学-动力工程及工程热物理] 

主　　题：gas turbine effusion cooling overall cooling effectiveness blowing ratio infrared imaging 

摘      要：Experimental investigations were performed on the overall cooling effectiveness η of a flat effusion wall over a wide range of blowing ratio(M=0.47～5.27).The effusion wall had a staggered multi-hole pattern typical of gas turbine combustor application,with a ratio of hole pitch to row spacing P/S=1∶2,a porosity PS/d2=72,and an inclination angle α=30°.The current paper documented distribution of the overall cooling effectiveness on the wall surface,based on infrared imaging of the 2-D surface temperature *** results indicate:(1) The overall η increases along with the streamwise distance for the wide range of M due to the superposition effect of the multi-row film cooling.(2) The overall η substantially benefits from the multi-hole inside convective *** hole convective cooling not only complements the weakest film protection at initial rows but also helps mitigate the temperature gradient.(3) The overall η increases asymptotically with increasing M,unlike adiabatic η mostly published in the past,which decreased after M reached a specific *** current work showcased the end cooling outcome jointly driven by the filming cooling mechanism and the hole inside convective cooling mechanism.