Flame Characteristics and Fuel Entrainment Inside a Cavity Flame Holder of a Scramjet Combustor

Lin, Kuo-Cheng; Tam, Chung-Jen; Boxx, Isaac; Carter, Campbell; Jackson, Kevin; Lindsey, Martin F.

doi:10.2514/6.2007-5381

Cited by 51 publications

(35 citation statements)

References 10 publications

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“…Results of a computation by Lin et al [45] highlighted the dependence of the cavity recirculation zone fuel distribution on upstream injector placement. Fueling the cavity from a set of injectors further upstream than the baseline injection case resulted in earlier merging of the fuel jets causing an effective aerodynamic blockage and subsequent reduction in air entrainment into the recirculation zone.…”

Section: Upstream Injectionmentioning

confidence: 97%

Cavity-based flameholding for chemically-reacting supersonic flows

Barnes

Segal

2015

Progress in Aerospace Sciences

179

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Section: Upstream Injectionmentioning

confidence: 97%

Cavity-based flameholding for chemically-reacting supersonic flows

Barnes

Segal

2015

Progress in Aerospace Sciences

179

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“…For studying supersonic combustion process, the structure and stabilizing position of the flame with different inflow Mach number, shape of cavity, fuel injection conditions and flame quenchinglimits were compared [2]. It was indicated that the flame was affected by the total fuel equivalence ratio and the flame would be stabilized near the bottom wall, aft wall and free shear layer of the cavity flame holder.…”

Section: Introductionmentioning

confidence: 99%

Flame quenching process in cavity based on model scramjet combustor

et al. 2012

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The flame quenching process in combustors was observed by high speed camera and Schlieren system, at the inflow conditions of Ma = 2.64, T 0 = 1 483 K, P 0 = 1.65 MPa, T = 724 K and P = 76.3 kPa. Changing process of the flame and shock structure in the combustor was clearly observed. The results revealed that the precombustion shock disappeared accompanied with the process in which the flame was blown out and withdrawed from the mainflow into the cavity and vanished after a short while. The time of quenching process was extended by the cavity flame holder, and the ability of flame holding was enhanced by arranging more cavities in the downstream as well. The flame was blown from the upstream to the downstream, so the flame in the downstream of the cavity was quenched out later than that in the upstream.

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“…7, No. 3;2013al., 2007Mathur et al, 1999). All the experiments presented above were performed on continuous facility, continuous facility can provide longer igniting time and ignition processe started at hot wall temperature condition which has been proved to be efficient methods to facilitate ignition at low total temperature inflow.…”

Section: Introductionmentioning

confidence: 99%

Experimental Research on Hydrogen and Hydrocarbon Fuel Ignition for Scramjet at Ma=4

Zhang¹,

Le²,

Yang³

et al. 2013

MAS

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Ignition experiments of Hydrogen and Ethylene were performed on direct-connected pulse combustion facility. Air stagnation temperatures were 900 K and stagnation pressures were 0.8 MPa, the entrance Mach number was approximate 2.0 provided by a two-dimension nozzle. The experimental results indicate that: (1) Hydrogen self-ignition won't occur at stagnation 935 K when it is injected upstream the cavity in this combustor model. But with low input power igniter, hydrogen can be ignited reliably. (2) Ethylene cannot be ignited with igniter only even at high igniter power. Under the assistant of both igniter and pilot Hydrogen, Ethylene can be ignited reliably and maintain stable combustion after the igniter and pilot hydrogen completely turned off. (3) The lowest equivalence ratio of pilot hydrogen for successful ethylene ignition is 0.05 below that ignition will fail. (4) When pilot hydrogen and igniters were both employed for ignition, the function of igniter is to ignite the hydrogen and the input power of igniter has no influence on ignition performance.

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Flame Characteristics and Fuel Entrainment Inside a Cavity Flame Holder of a Scramjet Combustor

Cited by 51 publications

References 10 publications

Cavity-based flameholding for chemically-reacting supersonic flows

Cavity-based flameholding for chemically-reacting supersonic flows

Flame quenching process in cavity based on model scramjet combustor

Experimental Research on Hydrogen and Hydrocarbon Fuel Ignition for Scramjet at Ma=4

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