Intake Fuel Injection and Shock Induced Combustion in a Scramjet Engine Model

Arai, T.; Masuda, Shōgo; Sakima, Fuminori

doi:10.2514/6.2003-6910

Cited by 3 publications

(3 citation statements)

References 2 publications

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“…These include ram accelerators [4,15,18,21], and oblique detonation wave engines (ODWEs) [1,3,10,29,30,32,33]. Experimental observations of oblique shock-induced detonation, such as those in [2,8,9,17,22,25] have shown that at least two different types of flow can arise. The first is the direct initiation of a detonation wave within a stagnation region.…”

Section: Literature Reviewmentioning

confidence: 98%

Detonation waves induced by a confined wedge

Fan

Wilson

2006

Aerospace Science and Technology

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Section: Literature Reviewmentioning

confidence: 98%

Detonation waves induced by a confined wedge

Fan

Wilson

2006

Aerospace Science and Technology

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“…Experimental observations of oblique shockinduced detonation [15][16][17][18][19][20] have shown that there are at least two different types of flow that can arise. The first is a direct initiation of a detonation wave within a stagnation region.…”

Section: Literature Reviewmentioning

confidence: 99%

Numerical modelling of oblique shock and detonation waves induced in a wedged channel

Fan

2008

Proceedings of the Institution of Mechanical Engineers, Part G:

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A computational study of wedge-induced oblique shock and detonation wave phenomena in the flow of a combustible mixture over a wedged channel is presented with the purpose of understanding the fundamental gasdynamics of the waves and their interactions. A two-dimensional, time accurate, finite-volume-based method was 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 • semi-angle and Mach numbers from 1.25 to 6, with other inflow parameters fixed. Within the computational domain either propagating or standing shock and detonation wave configurations were obtained depending on the flow Mach number and the wedge semi-angle. Four flow modes, namely, a propagating detonation wave, a standing detonation wave, a propagating shock wave, and a standing shock wave mode were identified. The two detonation-based modes were emphasized. Detonation initiation, propagation, and the induced wave interactions of these modes were investigated. The shock-based modes were also studied briefly. Phenomena explored included overall wave structures, detonation initiation arising from shock coalescence, location of initiation, and double detonation initiation. The physical mechanisms of these phenomena were analysed.

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“…In Ref. [ 6 ] as such initiating center the inlet cowl was used. At injection of hydrogen in to the flow before the cowl, the change of light in the channel was observed.…”

Section: Formulation Of Taskmentioning

confidence: 99%

Standing Sub-Compressed Detonation Wave in Hypersonic Combustible Mix Flow Sustained by Undercritical Microwave Discharge

Khodataev¹

2007

45th AIAA Aerospace Sciences Meeting and Exhibit

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This paper is devoted to theoretical study of detonation initiated in supersonic stream of air-propane mix at atmospheric pressure by microwave discharge pulse undercritical discharge. The designed numerical model of microwave discharge takes into account all main factors determining the properties of phenomenon. Plasma chemistry allows for ionization by electron impact, two-body and three-body attachment and recombination, molecular and electron excitation, dissociation etc. Plasma dynamics allows for transfer processes-gas viscosity, electron diffusion and thermal conductivity, and Ohm heating. It is one-liquid two-temperature model of combustible mix. Combustion is described by relax time depending on gas temperature and density. Electrodynamics takes into consideration the finite wavelength of radiation initiating and feeding the discharge, skin effect of inducted current at conditions of continuously changing electrical conductivity in discharge. The model uses real cross-sections of physical-chemical reactions, depending on calculated variables-density, gas temperature, electron temperature, and ionization and dissociation coefficients. Modeling confirms the microwave discharge ability to initiate detonation of stoichiometric mix of air and propane at speed of flow exceeding Chapmen-Jouguet value. This type of microwave discharge can be used for sustaining of standing plain or oblique stationary detonation wave in a hypersonic combustible flow at comparatively big cross-section. Pulse-periodical volumetric undercritical discharge with repetition frequency defined by size of averaged front depth of wave and flow speed is able to create periodically the net of ignition centers, which all together generate the common front. This stationary wave can be classified as subcompressed detonation wave and thus can be sustained at wide diapason of incoming flow velocity exceeding Chapman-Jouguet velocity.

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Intake Fuel Injection and Shock Induced Combustion in a Scramjet Engine Model

Cited by 3 publications

References 2 publications

Detonation waves induced by a confined wedge

Detonation waves induced by a confined wedge

Numerical modelling of oblique shock and detonation waves induced in a wedged channel

Standing Sub-Compressed Detonation Wave in Hypersonic Combustible Mix Flow Sustained by Undercritical Microwave Discharge

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