Visualization of flameholding mechanisms in a supersonic combustor using PLIF

Rasmussen, Chadwick C.; Dhanuka, Sulabh K.; Driscoll, James F.

doi:10.1016/j.proci.2006.08.007

Cited by 116 publications

(44 citation statements)

References 17 publications

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“…Driscoll and Rasmussen [16], Rasmussen et al [17,18], and Chadwick et al [19] showed that the correlations of premixed flame could not be directly applied to supersonic combustion, in which the fuel is injected into the airflow upstream or inside the cavity and the flame is actually non-premixed. Chadwick et al [19] have proposed a theoretical model to correlate the blowout equivalence ratio with the Damköhler number for the non-premixed flames of small-molecule fuels, such as hydrogen, ethylene, methane, and acetylene.…”

Section: Introductionmentioning

confidence: 99%

Blowout Limits of Cavity-Stabilized Flame of Supercritical Kerosene in Supersonic Combustors

Zhang

Wang

et al. 2014

Journal of Propulsion and Power

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Blowout limits of cavity-stabilized flame of supercritical kerosene were experimentally studied by using Mach 2.5 and 3.0 direct-connect supersonic model combustors operated under various air and fuel conditions. Specifically, the effects of the stagnation temperature and the stagnation pressure on the blowout limits were investigated for supercritical kerosene injected from the wall upstream of a cavity flameholder in a Mach 2.5 combustor. Experiments were performed under the same conditions for supercritical kerosene injected from the rear part of the cavity bottom to study the influence of the location of fuel injection. The blowout limits of supercritical kerosene injected from the wall upstream of the cavity were further investigated in a Mach 3.0 combustor. Besides the effects of the stagnation temperature and stagnation pressure, the effect of the divergence angle of the combustor on the lean-fuel blowout limit was studied. Results show that there exist two blowout limits corresponding to the lean-and rich-fuel conditions for a given stagnation temperature. The location of fuel injection has substantial influence on the blowout limits, whereas the influence of the stagnation pressure and the divergence angle of the combustor can be neglected in the range of interest.

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Section: Introductionmentioning

confidence: 99%

Blowout Limits of Cavity-Stabilized Flame of Supercritical Kerosene in Supersonic Combustors

Zhang

Wang

et al. 2014

Journal of Propulsion and Power

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“…For the case of non-premixed reactants, no single curve exists as that in the premixed cases. Recently Driscoll and Rasmussen et al [3][4][5][6] have carried out a series of theoretical and experimental studies on the lean blowout limits of cavity-stabilized flames for hydrogen, ethylene, methane and acetylene in a supersonic combustor. They showed that the stability limits were largely affected by the fuel injection location and thus the WSR model is not realistic for non-premixed flames.…”

Section: Introductionmentioning

confidence: 99%

“…4 Professor, National Key Laboratory of High Temperature Gas Dynamics, member AIAA. 5 Professor, National Key Laboratory of High Temperature Gas Dynamics.…”

Section: Introductionmentioning

confidence: 99%

Measurements of the Blowout Limits of Supercritical Aviation Kerosene in a Supersonic Combustor

Wang¹,

Fan²,

Zhang³

et al. 2011

47th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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Combustion and flame stability of supercritical kerosene were studied experimentally in a supersonic model combustor at various air and fuel conditions. The lean and rich blowout limits of supercritical kerosene injected from the bottom of a cavity flameholder were examined in Mach 2.5 airflow. It was found that the rich blowout limit was very sensitive to the stagnation temperature of the airflow while the lean limit was only slightly affected. Damkohler number was used to correlate the two limits. On the other hand, the lean blowout limits of supercritical kerosene injected upstream the cavity were investigated and compared at three different Mach numbers of 2.0, 2.5 and 3.0.

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“…It was demonstrated by Chadwick C.Rasmussen & Sulabh K. Dhanuka et al [31] that large CH2O signals can be obtained by increasing the camera gate duration to take advantage of the long fluorescence lifetime of formaldehyde at low pressure.…”

Section: Introductionmentioning

confidence: 99%

Recent Advances in Experimental and Numerical Analysis of Combustor Flow Fields in Supersonic Flow Regime

Pandey¹,

Singh²

2010

IJCEA

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Visualization of flameholding mechanisms in a supersonic combustor using PLIF

Cited by 116 publications

References 17 publications

Blowout Limits of Cavity-Stabilized Flame of Supercritical Kerosene in Supersonic Combustors

Blowout Limits of Cavity-Stabilized Flame of Supercritical Kerosene in Supersonic Combustors

Measurements of the Blowout Limits of Supercritical Aviation Kerosene in a Supersonic Combustor

Recent Advances in Experimental and Numerical Analysis of Combustor Flow Fields in Supersonic Flow Regime

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