11th European Conference on Turbomachinery Fluid dynamics & Thermodynamics

Paper ID:

ETC2015-254

Main Topic:

HEAT TRANSFER & COOLING

Authors

T.H. Wong - Department of Engineering Science, University of Oxford, UK
P.T. Ireland - Department of Engineering Science, University of Oxford, UK
K.P. Self - Rolls-Royce plc., UK

Abstract

The trailing edge of the high pressure turbine blade presents significant challenges to the turbine cooling engineer. The current research has focused specifically on the effect of cutback surface protuberance, or “land”, shapes on film cooling effectiveness. A set of six different land geometries has been investigated in a large scale model of the trailing edge pressure side ejection slot exit. Slot height and width and lip height was maintained. Pressure sensitive paint was used to measure adiabatic film cooling effectiveness at five blowing ratios ranging from 0.6 to 1.4 in increments of 0.2. High resolution 2D distributions of film cooling effectiveness both on the cutback surface and the top of the lands were recorded.

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