Date of Award

3-2013

Document Type

Thesis

Degree Name

Master of Science in Aeronautical Engineering

Department

Department of Aeronautics and Astronautics

First Advisor

Marc D. Polanka, PhD.

Abstract

The ultra compact combustor is a high performance gas turbine design concept that portends reduced weight for future weapons platforms. A natural outcome of the design is the continual presence of fuel-rich air in the turbine component of the engine. Because modern cooling schemes for hot section turbine blades involve injecting cool, oxygen-rich air adjacent to the surface, the potential arises for reaction with the unconsumed radicals in the mainstream ow and augmented heat transfer to the blade. This outcome is contrary to the purpose of film cooling, and can lead to early life-cycle turbine failure. This study examined the effects of multiple cooling hole geometries on downstream heat transfer. It demonstrated schemes that allow reactions to take place at a standoff distance from the wall being cooled and provide effective downstream cooling. Additionally, the research characterized the time scales involved in the reactions through temperature measurements and imaging.

AFIT Designator

AFIT-ENY-13-M-27

DTIC Accession Number

ADA584267

Download

Share

COinS