Accession Number:

ADA469258

Title:

Comparative Analysis of a High Bypass Turbofan Using a Pulsed Detonation Combustor

Descriptive Note:

Master's thesis

Corporate Author:

AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING AND MANAGEMENT

Personal Author(s):

• Andrus, Ionio Q.

Report Date:

2007-03-01

Pagination or Media Count:

143.0

Abstract:

It has been proposed that the implementation of a pulsed detonation combustor in a high-bypass turbofan engine would result in an engine that is both more efficient and more reliable. The validity of the performance claims are evaluated based on a comparison between the baseline and hybrid turbofans. The hybrid pulsed detonation engine was modeled in the Numerical Propulsion Simulation System NPSS and shares a common architecture with the baseline turbofan model, except that the combustor of the baseline engine is replaced with a pulsed detonation combustor. Detonation effects are calculated using a closed form solution of the Chapman-Jouguet Mach number with a total energy correction applied. Cycle time is calculated to provide a reasonable estimate of frequency for the user input geometry, and the losses due unsteady flow are accounted for by applying pressure and temperature losses to the fluid. A parametric study was performed to evaluate the effects of these losses on net thrust and TSFC. There is a definite level of acceptable loss that if surpassed makes pulsed detonation combustion a good candidate for inclusion into a hybrid turbofan engine.

Descriptors:

• *AIR BREATHING ENGINES
• *COMBUSTORS
• *AIR BREATHING ENGINES(UNCONVENTIONAL)
• *HIGH BYPASS TURBOFANS
• TURBOFAN ENGINES
• AIRCRAFT ENGINES
• DETONATIONS
• HYBRID PROPULSION
• HYBRID SIMULATION
• DETONATION WAVES
• THERMODYNAMIC CYCLES
• THESES
• COMBUSTION

Subject Categories:

• Computer Programming and Software
• Thermodynamics
• Air Breathing Engines (Unconventional)
• Combustion and Ignition
• Jet and Gas Turbine Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE