Date of Award

3-21-2013

Document Type

Thesis

Degree Name

Master of Science

Department

Department of Aeronautics and Astronautics

First Advisor

Paul I. King, PhD.

Abstract

A RDE has higher thermal efficiencies in comparison to its traditional gas turbine counterparts. Thus, as budgets decrease and fuel costs increase, RDEs have become a research focus for the United States Air Force. An integration assembly for attaching the first NGV section from a T63 gas turbine engine to a 6 inch diameter RDE was designed and built for this study. Pressure, temperature, and unsteadiness measurements were completed in this study to characterize the exhaust flow of the RDE through the NGVs. The experiment found that stagnation pressure dropped an average of 4% through the NGVs, and that unsteadiness as a measurement of dynamic pressure trace peak height was attenuated by a mean of 60% across the NGVs. Additionally, the study found the flow angle of the NGV exhaust to be between 40° and 55°. Finally, the study found that the RDE exhaust flow was approximately 2250°R before entering the NGVs

AFIT Designator

AFIT-ENY-13-M-09

DTIC Accession Number

ADA576030

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