Aerodynamic Characterization of a Cavity Flameholder in a Premixed Dual-Mode Scramjet

Kirik, Justin W.; Goyne, Christopher P.; McDaniel, James C.; Rockwell, Robert D.; Cantu, Luca; Gallo, Emanuela; Cutler, Andrew D.

doi:10.2514/1.b36605

Cited by 25 publications

(12 citation statements)

References 41 publications

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“…When the turbulence level is comparatively higher, the turbulent exchange of mass and energy between the cavity and mainstream is enhanced, promoting the interaction of combustion products in the recirculation zone with unburned reactants in the supersonic flow. 29 Thus, the kerosene in the supersonic mainstream could be ignited and an intense cavity shear layer flame is established near the cavity. For a tandem-cavity combustor, the large-scale eddies in the shear layer of the upstream cavity shed at the cavity aft wall and enter into the near-wall zone upstream of the downstream cavity.…”

Section: Resultsmentioning

confidence: 99%

Experimental investigation on the flame stabilization modes of liquid kerosene in a cavity-based scramjet combustor

Liu

Pan

et al. 2022

Proceedings of the Institution of Mechanical Engineers, Part G:

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The flame stabilization modes of liquid kerosene is investigated in a model scramjet combustor with flight condition of Ma 6. The effects of equivalence ratio and cavity configuration schemes on the flame stabilization modes are studied. Flame propagations and the evolution of the flow field from the ignition to the establishment of stable flame in the supersonic flow are acquired through high-speed photography and schlieren photography. Only cavity-recirculation-region stabilized combustion can be obtained in the single-cavity scramjet combustor. The intensity of combustion is weak and is termed as local ignition with low combustion efficiency. In the tandem-cavity scramjet combustor, the flame stabilization mode is largely determined by the total equivalence ratio. The flame could spread into the mainstream and even propagate against the supersonic flow as the equivalence ratio increases. The positive feedback mechanism between combustion and precombustion shock train is responsible for the evolutions of the flame stabilization modes, where the interactions between shock waves and turbulent boundary layer play a key role in the flame propagation process. The large-scale eddies in the shear layer of the upstream cavity shed at the cavity aft wall and could enhance the turbulent levels of the incoming flow of the downstream cavity. Consequently, an intense kerosene flame can be ignited in the tandem-cavity combustor. The flame could not spread to the mainstream in the single-cavity combustor due to the lower turbulence level weakening the interaction of combustion products in the recirculation zone with unburned reactants in the supersonic flow.

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Section: Resultsmentioning

confidence: 99%

Experimental investigation on the flame stabilization modes of liquid kerosene in a cavity-based scramjet combustor

Liu

Pan

et al. 2022

Proceedings of the Institution of Mechanical Engineers, Part G:

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show abstract

“…When the turbulence level is comparatively higher, the turbulent exchange of mass and energy between the cavity and mainstream is enhanced, promoting the interaction of combustion products in the recirculation zone with unburned reactants in the supersonic flow. 33 Thus the kerosene in the supersonic mainstream could be ignited and an intense cavity shear-layer flame is established near the cavity. For a dual-cavity combustor, the large-scale eddies in the shear layer of the upstream cavity shed at the cavity aft wall and enter into the near-wall zone upstream of the downstream cavity.…”

Section: The Discussion About the Ignition Limits And Combustion Stab...mentioning

confidence: 99%

Experimental investigation on the ignition limits of a kerosene-fueled cavity in model scramjet combustor

Liu

Pan

et al. 2023

Proceedings of the Institution of Mechanical Engineers, Part G:

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The ignition limits of liquid kerosene injected upstream of a cavity flameholder using a spark plug are investigated in a model scramjet combustor with the isolator entrance Mach number of 2.52, the total pressure of 1.6 MPa, and stagnation temperature of 1486 K. The effects of injection pressure and mixing distance on ignition are studied. Flame dynamics and the evolution of the flow field during the ignition process are acquired through high-speed photography and Schlieren photography. For near-field injection, successful ignition of kerosene can only be achieved when the injection pressure is extremely low or in a higher injection pressure range. The ignition is failed due to the fuel-rich local equivalence ratio in the cavity recirculation zone when the injection pressure is in the middle of injection pressure range. For far-field injection, the ignition trend is totally opposite compared with near-field injection. The ratio of the fuel that the cavity can react completely to that consumed by the mainstream is extremely low due to the minimal mass exchange rate between the cavity and the mainstream. The local equivalence ratio in cavity is the controlling factor determining whether successful ignition could be achieved. Only local ignition with low combustion efficiency is achieved in the present single-cavity combustor. The flame could not spread to the mainstream due to the lower turbulence level weakening the interaction of combustion products in the recirculation zone with unburned reactants in the supersonic flow.

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“…These complex flow physics span a wide range of length and time scales, requiring high-resolution experimental measurement techniques and numerical prediction tools. Current capabilities are limited to about 1 mm [3], i.e. the upper range of the turbulent spatio-temporal spectra including integral scales and larger intermediate scales, resulting in varied accuracy of the numerical tools and the need for new experimental data.…”

Section: Motivation and Research Questionmentioning

confidence: 99%

“…In-plane PIV resolution Laser sheet thickness Tracer Urban and Mungal [12] ~1 mm Unknown 15 nm TiO 2 Weisgerber et al [15] 0.5 mm 250 µm 12 nm Aerosil R812 Goyne et al [16] 1.2 mm 800 µm 0.3 µm Al 2 O 3 Scarano and Oudheusden [13] 420 µm estimated 500 µm 27 nm TiO 2 Scheel [17] 1 mm estimated 200 µm 12 nm Aerosil R812 Wagner et al [18] 1.78 mm 1.4 mm 0.02 µm Evonik P25 TiO 2 Tuttle et al [19] 1.81 mm 0.5 mm 100 nm TiO 2 Kirik et al [20] and Peltier and Carter [21] 0.96 mm 1 mm 100 nm TiO 2 Williams and Smits [14] 480 µm 1 mm 100 nm TiO 2 Kirik et al [3] 1 mm 0.3 mm Graphite nanoflakes…”

Section: Papermentioning

confidence: 99%

High-resolution PIV for characterization of the inflow to a cavity flameholder

Lieber

Goyne

Gibbons

2020

Meas. Sci. Technol.

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A methodology for the implementation of high-resolution, two-component, two-dimensional particle image velocimetry (PIV) in a high-speed, high-enthalpy flow is presented and demonstrated. The objective is to resolve the finer scales of combusting flows at high subsonic Mach numbers for accurate boundary conditions quantification for direct numerical simulations. A three-pronged approach consists of finding a near-optimum setup specific to the experiment, enhancing the raw signal with a novel filter for high-speed flows based on a logarithmic transform, and quantifying uncertainties. The methodology effectiveness is demonstrated with synthetic PIV, real PIV, and comparison with numerical simulations.

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Aerodynamic Characterization of a Cavity Flameholder in a Premixed Dual-Mode Scramjet

Cited by 25 publications

References 41 publications

Experimental investigation on the flame stabilization modes of liquid kerosene in a cavity-based scramjet combustor

Experimental investigation on the flame stabilization modes of liquid kerosene in a cavity-based scramjet combustor

Experimental investigation on the ignition limits of a kerosene-fueled cavity in model scramjet combustor

High-resolution PIV for characterization of the inflow to a cavity flameholder

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