Experimental and numerical study of near bleed hole heat transfer enhancement in internal turbine blade cooling channels

Abstract

This paper describes an experimental and numerical study of the heat transfer augmentation near the entrance to a gas turbine film cooling hole at different engine representative suction ratios (Vhole/V). For the experimental component the use of platinum thin film gauges and a transient testing technique were implemented to take measurements downstream of the film cooling hole entrance. Although this technique presents less detail than thermal crystals it however provides the capability of testing engine representative temperature ratios (Twall/Tgas). The numerical component of the study makes use of a commercial CFD code to predict heat transfer and flow characteristics near the hole's entrance