Flame Stabilization in High-Pressure Liquid Oxygen/Methane Rocket Engine Combustion

Lux, Johannes; Haidn, Oskar

doi:10.2514/1.36852

Cited by 55 publications

(13 citation statements)

References 19 publications

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“…Substantial experimental [8][9][10][11][12] and numerical [13][14][15] efforts on the characterization of propellant injection, mixing, and combustion processes at near-and supercritical conditions have recently led to improved understanding of the mechanisms involved. Most of these studies, however, have focused on shear coaxial injectors with light fluids, such as hydrogen and methane, as fuel.…”

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confidence: 99%

Supercritical Mixing and Combustion of Liquid-Oxygen/ Kerosene Bi-Swirl Injectors

Wang

Yang

2017

Journal of Propulsion and Power

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The mixing and combustion characteristics of liquid-oxygen/kerosene bi-swirl injectors are investigated under the supercritical conditions typical of contemporary rocket engines. The basis of the study is a large-eddy simulation technique combined with a unified treatment of real-fluid thermodynamics. The turbulence/chemistry interaction is treated using a laminar flamelet library approach. Emphasis is placed on the near-field flow and flame development downstream of the inner swirler. The flame is found to be stabilized by two counter-rotating vortices in the wake region of the liquid-oxygen post, which is covered by the kerosene-rich mixture. The width of the kerosene annulus is found to significantly affect the injector behavior. A wider annulus induces a larger spreading angle of the liquidoxygen stream, which intercepts the kerosene stream in a more efficient way. Increasing the annulus width, however, imposes a wake region in a broader zone. The resultant flame becomes relatively unstable if the flame thickness is larger than the liquid-oxygen post thickness. Variation of the kerosene annulus width has a negligible effect on the dominant frequency of the pressure fluctuation, but it changes the amplitude of fluctuation.

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confidence: 99%

Supercritical Mixing and Combustion of Liquid-Oxygen/ Kerosene Bi-Swirl Injectors

Wang

Yang

2017

Journal of Propulsion and Power

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“…Santos et al [11] developed a LRE with ethanol and GOX as propellants with variable thrust capacity of 50-100 kg. Tests conducted with a mixture ratio of 1.6, at four values of chamber pressure (8,10,12, and 15 bar), produced thrusts of 56, 70, 84, and 106 kg respectively. Flame stabilization near the injector face in a subscale optically accessible rocket, 50 mm in diameter and 430 mm long, was studied by Lux and Haidn [12].…”

Section: Introductionmentioning

confidence: 99%

“…Tests conducted with a mixture ratio of 1.6, at four values of chamber pressure (8,10,12, and 15 bar), produced thrusts of 56, 70, 84, and 106 kg respectively. Flame stabilization near the injector face in a subscale optically accessible rocket, 50 mm in diameter and 430 mm long, was studied by Lux and Haidn [12]. This 100 bar capacity rocket engine, with a throat diameter of 17.3 mm, was fuelled by methane and liquid oxygen (LOX).…”

Section: Introductionmentioning

confidence: 99%

Experimental and numerical investigation of combustion in a hydrocarbon and gaseous oxygen fuelled rocket

Shaikh

Patidar

Chowdhury

2017

Applied Thermal Engineering

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“…LES has been conducted by quite a few researchers [1][2][3][4][5] to improve our understanding of the fundamental mixing and combustion processes that are extremely difficult to measure experimentally. [6][7][8][9] The lack of comprehensive experimental data for the validation of supercritical LES undermines the credibility and hinders wider applications of LES of supercritical combustion to practical engine development. The fundamental modeling assumptions in LES of supercritical flow need to be carefully examined to ensure physical meaningful results are obtained from LES.…”

Section: Introductionmentioning

confidence: 99%

Several Fundamental Issues in Large Eddy Simulation of Supercritical Mixing and Combustion

Huo

Wang

Yang

2014

52nd Aerospace Sciences Meeting

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Large-Eddy Simulations (LES) of supercritical cold flow in a swirl injector with axi-symmetric configuration, and supercritical flames for LOX/methane stabilized after a splitter plate have been performed with various grid resolution. LES is used for turbulence closure. Three to four level of grid resolution is used to examine the grid sensitivity in both cold and reaction flows at supercritical conditions. One level of grid resolution corresponds to a 50% grid size decrease for all directions. In addition, the effect of ideal-gas and real-gas thermodynamic and transport property evaluations, sub-grid scale (SGS) models, and turbulent combustion models are also studied under reacting conditions. The results identify that the most important factor for accurate solutions is the grid resolution with the current numerical methodology. Turbulent combustion models are the second most important modeling factor. The effect of SGS models and property evaluation is much less important. To make high-fidelity modeling of supercritical mixing and combustion less expensive, so that they can be widely used in solving practical problems associated with supercritical mixing and combusting , appropriate models are needed to alleviate the grid resolution requirement.

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Flame Stabilization in High-Pressure Liquid Oxygen/Methane Rocket Engine Combustion

Cited by 55 publications

References 19 publications

Supercritical Mixing and Combustion of Liquid-Oxygen/ Kerosene Bi-Swirl Injectors

Supercritical Mixing and Combustion of Liquid-Oxygen/ Kerosene Bi-Swirl Injectors

Experimental and numerical investigation of combustion in a hydrocarbon and gaseous oxygen fuelled rocket

Several Fundamental Issues in Large Eddy Simulation of Supercritical Mixing and Combustion

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