Blowout Limits of Supersonic Cavity-Stabilized Flames

Rasmussen, Chadwick C.; Driscoll, James F.; Donbar, Jeffrey M.; Gruber, Mark; Hsu, Kuang–Yu; Carter, C.

doi:10.2514/6.2004-3660

Cited by 4 publications

(1 citation statement)

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“…and the heat release region and combustion zone were consequently illustrated [3]. Also, the emission of the strut flame at the nozzle exit in which the velocity was supersonic has been observed by high speed camera [4]. Based on in-depth research on the supersonic combustion process and flame stabilization, we can understand more clearly the flame structure of the unpremixed supersonic combustion [5].…”

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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Section: Introductionmentioning

confidence: 99%