Experimental Investigation of Turning Flow Effects on Innovative Trailing Edge Cooling Configurations With Elliptic Pin Fins

Abstract

This paper describes a heat transfer experimental study of two trailing edge cooling configurations that reproduce two real geometries of aeronautical engine blades. The cooling systems consist of 5 rows of elliptical pin fins with the main axis that is streamwise or spanwise oriented inserted in a wedge shaped duct and followed by an array of circular pin fins with a fillet radius. The test rig reproduces a real trailing edge layout: the airflow enters the trailing edge in the radial direction with a 90° tuning flow from the hub inlet to the trailing edge outlet; a tip outlet is also present to investigate its effects on heat transfer and pressure drop.