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


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/a469258.pdf


Report Date : Mar 2007


Pagination or Media Count : 143


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