Accession Number : ADA576030


Title :   Characterization of Rotating Detonation Engine Exhaust Through Nozzle Guide Vanes


Descriptive Note : Master's thesis


Corporate Author : AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH GRADUATE SCHOOL OF ENGINEERING AND MANAGEMENT


Personal Author(s) : DeBarmore, Nick D


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/a576030.pdf


Report Date : 21 Mar 2013


Pagination or Media Count : 63


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 deg and 55 deg. Finally, the study found that the RDE exhaust flow was approximately 2250 deg R before entering the NGVs.


Descriptors :   *GUIDE VANES , *JET ENGINE EXHAUST , COMPARISON , DYNAMIC PRESSURE , EFFICIENCY , GAS TURBINES , NOZZLES , STAGNATION PRESSURE , THERMAL PROPERTIES , THESES , TURBOMACHINERY


Subject Categories : Aircraft


Distribution Statement : APPROVED FOR PUBLIC RELEASE