Date of Award

3-10-2010

Document Type

Thesis

Degree Name

Master of Science in Aeronautical Engineering

Department

Department of Aeronautics and Astronautics

First Advisor

Paul I. King, PhD

Abstract

Past research has indicated that implementation of a pulsed detonation combustor (PDC) into a high-bypass turbofan engine yields a more efficient engine at design conditions. It is proposed that performance gains can be made utilizing this hybrid engine off-design. A hybrid high-bypass turbofan engine with a PDC model was evaluated for a range of Mach numbers, altitudes, and fill fractions in the Numerical Propulsion System Simulation (NPSS). Results were compared to a conventional baseline high-bypass turbofan engine that shares the same architecture with the hybrid. The NPSS baseline engine was validated using the Aircraft Engine Design System (AEDsys) program and the net thrust and specific fuel consumption agreed to within one percent. The effect of detonation on the core air flow is calculated using a closed form solution for the Chapman-Jouguet Mach number with a total energy correction applied. Results indicate that fill fraction can be adjusted to reduce the TSFC to that of the baseline engine and lower at some thrust levels. With careful selection of design parameters, results suggest a pulsed detonation combustor may be an appropriate candidate for inclusion in a hybrid turbofan engine.

AFIT Designator

AFIT-GAE-ENY-10-M26

DTIC Accession Number

ADA516702

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