Numerical investigation of turbulent hydrogen combustion in a SCRAMJET using flamelet modeling

Oevermann, Michael

doi:10.1016/s1270-9638(00)01070-1

Cited by 287 publications

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“…To solve this problem, some fuel injection techniques have been proposed. The strut [5][6][7][8][9][10][11][12][13][14], the cavity [15][16][17][18], the cantilevered ramp [4], the backward facing step [19][20][21] and the combination [22][23][24][25], whose principle is to generate vorticity in the vicinity of the walls of the combustor. The region forming the vorticity, namely the recirculation zone, has low flow velocity.…”

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confidence: 99%

“…Zou et al [6] have used a newly-proposed partiallyresolved numerical simulation procedure to investigate turbulent combustion in a two-dimensional DLR scramjet engine, and the large-scale turbulence was defined by the temporal filtering. Oevermann [7] has used a two-equation k- turbulence model combined with a stretched laminar …”

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confidence: 99%

“…Oevermann [7] has used a two-equation k- turbulence model combined with a stretched laminar flamelet model to simulate the turbulent diffusion flames in a strut-based scramjet combustor. The commercial software Fluent has been applied to study the mixing and combustion characteristics of kerosene in a strut-based full-scale supersonic combustor along with the single-step laminar finiterate kinetics, with calculations performed using the oneequation Spalart-Allmaras model [8].…”

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Parametric effects on the combustion flow field of a typical strut-based scramjet combustor

et al. 2011

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The flame-holding mechanism in hypersonic propulsion technology is the most important factor in prolonging the duration time of hypersonic vehicles. The two-dimensional coupled implicit Reynolds-averaged Navier-Stokes equations, the shear-stress transport k- turbulence model and the finite-rate/eddy-dissipation reaction models were used to simulate the combustion flow field of a typical strut-based scramjet combustor. We investigated the effects of the hydrogen-air reaction mechanism and fuel injection temperature and pressure on the parametric distributions in the combustor. The numerical results show qualitative agreement with the experimental data. The hydrogen-air reaction mechanism makes only a slight difference in parametric distributions along the walls of the combustor, and the expansion waves and shock waves exist in the combustor simultaneously. Furthermore, the expansion wave is formed ahead of the shock wave. A transition occurs from the shock wave to the normal shock wave when the injection pressure or temperature increases, and the reaction zone becomes broader. When the injection pressure and temperature both increase, the waves are pushed out of the combustor with subsonic flows. When the waves are generated ahead of the strut, the separation zone is formed in double near the walls of the combustor because of the interaction of the shock wave and the boundary layer. The separation zone becomes smaller and disappears with the disappearance of the shock wave. Because of the horizontal fuel injection, the vorticity is generated near the base face of the strut, and this region is the main origin for turbulent combustion. , hypersonic propulsion technology has drawn increasing attention from researchers. However, the flame-holding mechanism in the scramjet combustor cannot satisfy the requirement for cruising a long time in near-space [3] because of the short residence time of the mixture remaining in the supersonic flow, which is in the order of milliseconds [4]. This restricts improvement of the aerodynamic performance of hypersonic vehicles. To solve this problem, some fuel injection techniques have been proposed. The strut [5][6][7][8][9][10][11][12][13][14], the cavity [15][16][17][18], the cantilevered ramp [4], the backward facing step [19][20][21] and the combination [22][23][24][25], whose principle is to generate vorticity in the vicinity of the walls of the combustor. The region forming the vorticity, namely the recirculation zone, has low flow velocity. In this region the fuel mixes with the supersonic flow and the mixture can stay in the scramjet combustor for a long time. Zou et al. [6] have used a newly-proposed partiallyresolved numerical simulation procedure to investigate turbulent combustion in a two-dimensional DLR scramjet engine, and the large-scale turbulence was defined by the temporal filtering. Oevermann [7] has used a two-equation k- turbulence model combined with a stretched laminar

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Parametric effects on the combustion flow field of a typical strut-based scramjet combustor

et al. 2011

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“…A 2D RANS calculation of Oevermann (2000) shows agreement with the experimental data, but the calculated static temperature profiles in the far downstream of the strut overshoot the experimental data, possibly because the effective overall equivalence ratio in his calculation is higher than the experimental value. Potturi and Edwards (2012) found that their RANS calculation yields better predictions to the velocity profiles but worse time-averaged static temperature than their LES/RANS simulation.…”

Section: Introductionmentioning

confidence: 78%

“…As shown in Figure 2, the 2D slot is evenly divided into 52 portions and sonic hydrogen flow is injected from the other two portions, the others being treated as solid walls. Such an injection scheme produces the overall equivalence ratio in the present 2D calculation, the same as the experimental one (0.034), which is however not reproduced in the 2D RANS calculation of Oevermann (2000). In the present study, a block structured hexahedral grid is employed for all mesh generations.…”

Section: Computational Specificationsmentioning

confidence: 86%

Numerical Investigation on Flame Stabilization in DLR Hydrogen Supersonic Combustor with Strut Injection

Zhang

Yao

et al. 2017

Combustion Science and Technology

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Flame stabilization in the DLR hydrogen supersonic combustor with strut injection was numerically investigated by using an in-house large eddy simulation code developed on the OpenFoam platform. To facilitate the comparison and analysis of various hydrogen oxidation mechanisms with different levels of mechanism reduction, the proposed 2D calculation model was validated against both the 3D simulation and the experimental data. The results show that the 2D model can capture the DLR flow and combustion characteristics with satisfactorily quantitative accuracy and significantly less computational load. By virtue of the flow visualization and the analyses of species evolution and heat release, the supersonic combustion in the DLR combustor can be divided into three stages along the streamwise direction: the induction stage where ignition occurs and active radicals are produced, the transition stage through which radicals are advected to the downstream, and the intense combustion stage where most heat release occurs. Furthermore, the sensitivity analysis of key reaction steps identifies the important role of chain carrying and heat release reactions in numerically reproducing the three-stage combustion stabilization mode in the DLR combustor.ARTICLE HISTORY

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Investigation of flow characteristics in supersonic combustion ramjet combustor toward improvement of combustion efficiency

et al. 2020

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Supersonic combustion ramjet (scramjet) is a variant of ramjet in which the combustion takes place at supersonic velocity. The flow physics inside the scramjet combustor is quite complex due to the fact that the mixing and completion of the combustion take place in a short time, which is of the order of milliseconds. This study focuses on flow characteristics within the combustion chamber of the scramjet engine that is designed to improve energy efficiency by enhancing combustion efficiency. The effect on combustion performance and thereby the energy efficiency on using strut-based flame stabilizer is evaluated at different positions. Reynolds averaged Navier-Stokes equations are solved with the Shear Stress Transport k-ω turbulence model. Single strut configuration is used to validate with the experimental data. Single strut is then compared with three-strut configuration. In the three-strut configuration, the location of the primary strut is kept constant, and the secondary struts are relocated in x and y directions. Combustion performance was evaluated for the cases of flow from primary strut only and through three struts. It was found that the placement of secondary strut in a three-strut configuration plays a vital role in improving energy efficiency. A maximum of 33.86% improvement in combustion efficiency was observed in comparison to the single strut combustor. A reduction in unburned fuel was observed, making the system more energy efficient. If the struts are not placed optimally, the combustion performance of the combustor was observed to be lower than that of a single-strut configuration. The shock reflection and expansion fans within the primary combustion zone and the secondary strut region enhance the combustion efficiency. The wall static pressure was observed to increase with the addition of secondary struts. For certain strut configurations, flow separation was seen on the combustor walls. If the secondary strut was placed close to the primary strut, combustion efficiency was found to enhance. It was seen that

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Numerical investigation of turbulent hydrogen combustion in a SCRAMJET using flamelet modeling

Cited by 287 publications

References 0 publications

Parametric effects on the combustion flow field of a typical strut-based scramjet combustor

Parametric effects on the combustion flow field of a typical strut-based scramjet combustor

Numerical Investigation on Flame Stabilization in DLR Hydrogen Supersonic Combustor with Strut Injection

Investigation of flow characteristics in supersonic combustion ramjet combustor toward improvement of combustion efficiency

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