Date of Award

6-19-2014

Document Type

Thesis

Degree Name

Master of Science

Department

Department of Aeronautics and Astronautics

First Advisor

Marc D. Polanka, PhD.

Abstract

The demand for increased thrust, higher engine efficiency, and reduced fuel consumption has increased the turbine inlet temperature and pressure in modern gas turbine engines. The outcome of these higher temperatures and pressures is the potential for unconsumed radical species to enter the turbine. Because modern cooling schemes for turbine blades involve injecting cool, oxygen rich air adjacent to the surface, the potential for reaction with radicals in the mainstream flow and augmented heat transfer to the blade arises. This study evaluated various configurations of multiple cylindrical rows of cooling holes in terms of both heat release and effective downstream cooling. It confirmed that a build-up of rows of coolant could be used to effectively protect the wall in a fuel-rich environment. It demonstrated slot and trench configurations to be effective in reducing the heat flux to the wall. Also, the Swirler and Two Row Upstream configurations were shown to highly increase radical consumption. Finally, this research developed infrared imaging as a technique for evaluating the wall temperature of the film cooled surface.

AFIT Designator

AFIT-ENY-14-J-37

DTIC Accession Number

ADA602973

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