Numerical simulation of transient combustion process in pulse detonation engine

Kim, HyungWon; Anderson, Dale; Lu, Frank K.; Wilson, Donald R.

doi:10.2514/6.2000-887

Cited by 9 publications

(38 citation statements)

References 4 publications

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“…Our previous work using the same numerical technique suggests that a transition phenomenon can be captured. 17,22 The rapid transition in the present simulations supports the experimental observation by Lu and Wilson 23 that shock-induced detonation occurs almost instantly and seems to indicate that a direct initiation is possible with shock-induced detonation. In the present study, we propose the possibility that the impingement of an oblique shock initiates combustion.…”

Section: Resultssupporting

confidence: 78%

“…The numerical method taken to perform the required computations is a two-dimensional, time accurate, finite-volume-based method developed by Kim at al. 17 A schematic of the configuration is shown in Fig. 1 with a straight end-section symmetrically arranged within a straight chamber.…”

Section: Methodsmentioning

confidence: 99%

“…The numerical technique was previously reported in Kim et al 17 and only a brief overview is provided here. The timedependent two-dimensional Euler equations are used to describe an inviscid, non-heat-conducting, reacting gas flow in which thermal non-equilibrium is modeled with a twotemperature model.…”

Section: A Model Equationsmentioning

confidence: 99%

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Numerical Study of Reactive Flow Past a Wedge in a Channel

Fan

Lu²

2005

43rd AIAA Aerospace Sciences Meeting and Exhibit

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Detonation of the flow of a combustible mixture over a wedged channel is numerically simulated. A two-dimensional, time accurate, finite-volume-based method is used to perform the computations, and a five-species, two-step chemical reaction is assumed for a stoichiometric hydrogen-air mixture. The combustion channel is made of a wedged section followed by a constant area section. The simulation was performed with wedges of up to 20 deg semi-angle and Mach numbers from 2 to 6.5, with other inflow parameters fixed. Different types of flows arise depending on the wedge angle and the incoming Mach number. Propagating and standing detonation waves modes were found, both of which can be further subdivided, depending on where the detonation is initiated. Moreover, a case without combustion was discovered for a narrow range of Mach numbers for the 5 deg wedge.

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Section: Resultssupporting

confidence: 78%

Section: Methodsmentioning

confidence: 99%

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Numerical Study of Reactive Flow Past a Wedge in a Channel

Fan

Lu²

2005

43rd AIAA Aerospace Sciences Meeting and Exhibit

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“…The numerical technique was previously reported in [11,19,20] and only a brief overview is provided here. The timedependent two-dimensional Euler equations are used to describe an inviscid, non-heat-conducting, reacting gas flow with a two-temperature model for thermal non-equilibrium.…”

Section: Model Equations and Numerical Considerationsmentioning

confidence: 99%

Detonation waves induced by a confined wedge

Fan

Wilson

2006

Aerospace Science and Technology

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“…Previously, Kim et al 2 developed a code for a two-dimensional, inviscid, chemically reacting flow. A thermally and chemically non-equilibrium flow with a two-temperature model and a two-step hydrogen-air reaction model was used to simulate the flow in a pulsed detonation engine.…”

Section: Introductionmentioning

confidence: 99%

Numerical Study of Two-Dimensional Viscous, Chemically Reacting Flow

Anderson

Wilson³

et al. 2005

17th AIAA Computational Fluid Dynamics Conference

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A computational fluid dynamics code for two-dimensional, multi-species, laminar NavierStokes equations is developed to simulate a pulsed detonation based propulsion system and to analyze its performance. 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 second-order central finite difference method. Chemical kinetics for hydrogen-air mixture is modeled using GRI-Mech. Code validation and investigation of a pulsed normal detonation wave engine for inviscid and viscous cases are accomplished in this work. The code is ported to a high-performance parallel machine with Message-Passing Interface.

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Numerical simulation of transient combustion process in pulse detonation engine

Cited by 9 publications

References 4 publications

Numerical Study of Reactive Flow Past a Wedge in a Channel

Numerical Study of Reactive Flow Past a Wedge in a Channel

Detonation waves induced by a confined wedge

Numerical Study of Two-Dimensional Viscous, Chemically Reacting Flow

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