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Numerical Study Of Chemically Reacting Viscous Flow Relevant To Pulsed Detonation Engines

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Numerical Study Of Chemically Reacting Viscous Flow Relevant To Pulsed Detonation Engines

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dc.contributor.author Yi, Tae-Hyeong en_US
dc.date.accessioned 2007-08-23T01:56:01Z
dc.date.available 2007-08-23T01:56:01Z
dc.date.issued 2007-08-23T01:56:01Z
dc.date.submitted December 2005 en_US
dc.identifier.other DISS-1198 en_US
dc.identifier.uri http://hdl.handle.net/10106/77
dc.description.abstract A computational fluid dynamics code for two-dimensional, multi-species, laminar Navier-Stokes equations is developed to simulate a recently proposed engine concept for a pulsed detonation based propulsion system and to investigate the feasibility of the engine of the concept.The governing equations that include transport phenomena such as viscosity, thermal conduction and diffusion are coupled with chemical reactions. The gas is assumed to be thermally perfect and in chemically non-equilibrium. The stiffness due to coupling the fluid dynamics and the chemical kinetics is properly taken care of by using a time-operator splitting method and a variable coefficient ordinary differential equation solver. A second-order Roe scheme with a minmod limiter is explicitly used for space descretization, while a second-order, two-step Runge-Kutta method is used for time descretization. In space integration, a finite volume method and a cell-centered scheme are employed. The first-order derivatives in the equations of transport properties are discretized by a central differencing with Green's theorem. Detailed chemistry is involved in this study. Two chemical reaction mechanisms are extracted from GRI-Mech, which are forty elementary reactions with thirteen species for a hydrogen-air mixture and twenty-seven reactions with eight species for a hydrogen-oxygen mixture. The code is ported to a high-performance parallel machine with Message-Passing Interface. Code validation is performed with chemical kinetic modeling for a stoichiometric hydrogen-air mixture, an one-dimensional detonation tube, a two-dimensional, inviscid flow over a wedge and a viscous flow over a flat plate. Detonation is initiated using a numerically simulated arc-ignition or shock-induced ignition system. Various freestream conditions are utilized to study the propagation of the detonation in the proposed concept of the engine. Investigation of the detonation propagation is performed for a pulsed detonation rocket and a supersonic combustion chamber. For a pulsed detonation rocket case, the detonation tube is embedded in a mixing chamber where an initiator is added to the main detonation chamber. Propagating detonation waves in a supersonic combustion chamber is investigated for one- and two-dimensional cases. The detonation initiated by an arc and a shock wave is studied in the inviscid and viscous flow, respectively. Various features including a detonation-shock interaction, a detonation diffraction, a base flow and a vortex are observed. en_US
dc.description.sponsorship Wilson, Donald en_US
dc.language.iso EN en_US
dc.publisher Aerospace Engineering en_US
dc.title Numerical Study Of Chemically Reacting Viscous Flow Relevant To Pulsed Detonation Engines en_US
dc.type Ph.D. en_US
dc.contributor.committeeChair Wilson, Donald en_US
dc.degree.department Aerospace Engineering en_US
dc.degree.discipline Aerospace Engineering en_US
dc.degree.grantor University of Texas at Arlington en_US
dc.degree.level doctoral en_US
dc.degree.name Ph.D. en_US
dc.identifier.externalLink https://www.uta.edu/ra/real/editprofile.php?onlyview=1&pid=268
dc.identifier.externalLinkDescription Link to Research Profiles

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