Heat transfer and aerodynamics studies of multiple cooling holes

Abstract

This paper presents a heat transfer and details flowfield measurements of multiple cooling holes. Normal cylindrical hole with steeper inclined angle of 20° arranged to perform a 5 times 4 cooling holes matrix have been considered. Experiments have been done at a single Reynolds number base on the hole diameter equal to 6200 at three blowing ratios of 0.5, 1.0 and 2.0 for the heat transfer and only for the later two for aerodynamics measurements. The heat transfer experiments involved the IR camera to capture the surface temperature data while the aerodynamics experiments involved the three dimensional Laser Doppler Velocimeter for velocity measurements. Results of heat transfer consists of overall film cooling effectiveness distribution and laterally average film cooling effectiveness in x-direction represented by a contour plot and a graph respectively. Four measurement planes have been considered in the aerodynamics experiments which are located at x/D = 7, 17, 27 and 37. The aerodynamics results presented in this paper include of various contour plots which represent the distribution of normalize velocity for u, v, and w components, normalize root mean square velocity for u, v, and w components and the Reynolds stress tensor. Both set of results have been discussed in such, a clear relation between the flow behavior and heat transfer phenomena have been established. Copyright © 2012 Gas Turbine Society of Japan.