Operational Sensitivities of an Integrated Scramjet Ignition/Fuel-Injection System

Gallimore, S. D.; Jacobsen, Lance; O’Brien, Walter F.; Schetz, Joseph A.

doi:10.2514/2.6116

Cited by 34 publications

(15 citation statements)

References 8 publications

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“…Such chemistry is already incorporated in Marinov's model [23]. Our previous paper [12] showed that low-temperature chemistry played an important role in the catalytic effect resulting from the addition of NO x . As for DME, the NO x effect was not investigated because the reaction model did not include the NO x chemistry.…”

Section: Numerical Methods and Kinetic Modelsmentioning

confidence: 97%

“…In the case of fuel injection upstream of the PJ [9][10][11][12][13][14], the PJ acted as a flameholder and strong combustion easily occurred even for CH 4 , the ignition delay of which was the longest among the hydrocarbon fuels. The flame region widely spread after local ignition at the site at which the fuel jet directly collided with the PJ.…”

Section: Ignition Test Of Fuel Injected Upstream Of Pjmentioning

confidence: 99%

“…It is well known that the existence of a small number of radicals drastically reduces ignition delay time of the fuel [8,9]. Ignition tests of low-hydrocarbon fuels such as CH 4 and C 2 H 4 by the PJ torch [10][11][12][13][14][15] in a supersonic flow and theoretical analyses of the effects of the addition of radicals and NO x on ignition delay of the fuels [13][14][15] have been widely conducted by many researchers, including the authors.…”

Section: Introductionmentioning

confidence: 99%

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Suitability of C2-, C3-Hydrocarbon Fuels for Plasma Ignition in High-Speed Flow

Takita

Ohashi

Abe

2009

Journal of Propulsion and Power

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The suitability of hydrocarbon fuels for plasma ignition in high-speed flow was numerically and experimentally investigated. Numerical analysis of ignition delay time showed that the effects of additions of radicals and NO x on ignition delay times of C 3 H 8 and dimethyl ether were very slight in comparison with those for C 2 H 4 . Ignition tests of C 3 H 8 and dimethyl ether fuels by a plasma jet torch in a supersonic flow confirmed such a low sensitivity to additions of radicals and NO x . The amounts of combustion of C 3 H 8 ignited by the plasma jet were smaller than that of C 2 H 4 , though ignition delay times of those fuels without radical addition were almost the same as that of C 2 H 4 . In the case of fuel injection upstream of the plasma jet, the amounts of combustion of C 3 H 8 and dimethyl ether fuels increased with the mole fraction of O 2 in the feedstock gas to the plasma jet torch, the same as with CH 4 and C 2 H 4 . This result indicates that the local O 2 concentration around the igniter is very important for success in attainment of strong combustion and flameholding in a high-speed flow.Nomenclature E.R. = equivalence ratio C = mole fraction P in = electric power input p t0 = total pressure of main flow p w = wall pressure p 0 = system pressure or initial pressure T 0 = initial temperature x i = position of fuel injector

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Section: Numerical Methods and Kinetic Modelsmentioning

confidence: 97%

Section: Ignition Test Of Fuel Injected Upstream Of Pjmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Suitability of C2-, C3-Hydrocarbon Fuels for Plasma Ignition in High-Speed Flow

Takita

Ohashi

Abe

2009

Journal of Propulsion and Power

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“…The flow field in a scramjet engine is transitional over a wide range of speed, and in this range engine performance is characterized by complex transitional fluid dynamics, supersonic/subsonic flows with the corresponding shock fields, 10 coupled heat release/shock generation, combustion thermodynamics and chemical reactions. 11 So there are benefits from thinking scramjet engines in terms of continuum mechanics with distributed parameter control. To help solve the problems existing in the combustion control of scramjet engines, Daren et al 12 and Tao et al 13 made some suggestions from a viewpoint of applying distributed parameter control technologies to the control of scramjet engines, and the studies have provided an initial proof of the validity of distributed parameter control for scramjet engines.…”

Section: Introductionmentioning

confidence: 99%

Simplified procedure for controlling pressure distribution of a scramjet combustor

Cui

2014

Chinese Journal of Aeronautics

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Scramjet engines are used at extreme temperatures and velocity. New control problems involving distributed parameter control have been found concerning investigations of the control of scramjet engines whose physical states are spatially interacted. Succeeding the existing theoretical studies on the distributed parameter control for scramjet engines, this paper puts forward a simplified distributed parameter control approach for scramjet engines aimed at engineering application. The simplified control procedure uses the classical proportional-integral (PI) compensation to control the target pressure distribution of scramjet engines, which is effective and applicable for practical implements. Simulation results show the validation of the simplified distributed parameter control procedure.

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“…The development of the techniques of ignition control and combustion stabilization in near-wall supersonic air flow zones and combustion entrainment from a wall zone directly into the supersonic flow is of great interest. Wall flows in which fuel (hydrogen, methane, or ethylene) injection across the flow is combined with a plasma jet driven by an electric-arc source and also projected across the main flow have been investigated in a series of studies (see, for example, [1][2][3][4][5][6]). Judging from the arc source parameters used, the sources injected a plasma in which the electron temperature was close to the temperature of the heavy components.…”

mentioning

confidence: 99%

Investigation of flows past a plate in the presence of exoergic processes driven by the interaction between a nonequilibrium electric discharge and a propane-air mixture

Ivanov¹,

Коган²,

Скворцов³

2006

Fluid Dyn

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Supersonic flow (M = 2) past a plate along which propane is injected is investigated within the framework of the solution of problems of combustion initiation and stabilization at low static temperatures and pressures in the presence of a nonequilibrium discharge and metal and dielectric interceptors mounted on the plate surface. The experiments show that two zones with exoergic reactions develop when a metal interceptor is mounted on the plate. One zone is located ahead of the leading separation zone and the other above and behind the interceptor edge, its boundary partially penetrating into the supersonic flow region. Using modern spectroscopic methods, the radiation intensity distributions of a series of plasmochemical reaction products are obtained in the neighborhood of the plate ahead of the interceptor, behind it, and above its edge. It is found that the fuel is intensively converted under the action of the discharge with the occurrence of a series of free radicals, atomic hydrogen and oxygen which are themselves chemically active.

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Operational Sensitivities of an Integrated Scramjet Ignition/Fuel-Injection System

Cited by 34 publications

References 8 publications

Suitability of C2-, C3-Hydrocarbon Fuels for Plasma Ignition in High-Speed Flow

Suitability of C2-, C3-Hydrocarbon Fuels for Plasma Ignition in High-Speed Flow

Simplified procedure for controlling pressure distribution of a scramjet combustor

Investigation of flows past a plate in the presence of exoergic processes driven by the interaction between a nonequilibrium electric discharge and a propane-air mixture

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