Combustion characteristics of hydrogen and cracked kerosene in a DLR scramjet combustor using hybrid RANS/LES method

Shin, Junsu; Sung, Hong-Gye

doi:10.1016/j.ast.2018.03.006

Cited by 30 publications

(6 citation statements)

References 23 publications

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“…This hybrid method uses a transition function 34 of the distance to the wall, which combines the Spalart–Allmaras (S-A) RANS model 35 near the wall and the Yoshizawa sub-grid model 36 far from the wall. Although the RANS model may neglect the turbulence and combustion interaction, the computational load caused by grid refinement near the wall would be greatly reduced, and similar treatments 37,38 have been used widely for the same purpose. Meanwhile, the RANS model simulates only a very thin layer near wall (∼0.1 δ inf ), its impacts do not count for much.…”

Section: Experimental Description and Numerical Treatmentmentioning

confidence: 99%

Effects of cavity parameters on flame flashback phenomenon in a supersonic crossflow with a cavity flameholder

Tang

Zhao

Wang

et al. 2022

Proceedings of the Institution of Mechanical Engineers, Part G:

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In this paper, the cavity parameters of length-to-depth ratio, aft ramp angle, and nitrogen throttling positions are numerically studied by a Large Eddy Simulation (LES) combined with the Flamelet/Progress Variable (FPV) model, to investigate the inducing factors and formation mechanism of flame flashback. These numerical studies are validated and compared to our previous experiments. It can be observed from both the calculated and experimental flow field that the larger length-to-depth ratio, sharper aft ramp angle, and nitrogen throttling closer to the cavity strengthen the mixing of fuel wake and promote the jet penetration depth. Meanwhile, the separation of the boundary layer downstream of the cavity can be induced by the shear layer, acoustic oscillation, as well as nitrogen throttling. And the above favorable prerequisites enhance the heat release nearby, while the reverse pressure gradient causes the enlargement of the boundary layer separation in turn. Under this positive feedback, thermal choking is formed and drives the reverse propagation of the high-temperature flame. It is concluded that the downstream boundary layer separation induced by the changes of the cavity parameters is a prerequisite for the flame flashback, and the formation of the thermal choking is the main reason for the flame flashback.

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Section: Experimental Description and Numerical Treatmentmentioning

confidence: 99%

Effects of cavity parameters on flame flashback phenomenon in a supersonic crossflow with a cavity flameholder

Tang

Zhao

Wang

et al. 2022

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…To eliminate the computational cost, computational fluid dynamics based solver [1][2][3][4][5][6] has been taken more attention. Various computational combustion methods [7][8][9][10] are available. Species transport modelling is taking more attention which gives similar results as in experimental data.…”

Section: Introductionmentioning

confidence: 99%

Impact of parametric variation on combustion characteristics of hydrogen‐fueled strut based scramjet combustor at supersonic speed

2020

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Supersonic combustion ramjet engine is more fascinating among all the airbreathing engines. Due to its higher thrust to weight ratio, researchers are more interested to get the superior combustion performance at the optimum boundary conditions. The flow field characteristics and combustion performance have been analysed with the help of Ansys 14.0 software. Generic scramjet combustor of German Aerospace Center (DLR) has been taken into consideration for comparison purpose and off design analysis has been conducted to investigate and analyse the changes. Two dimensional compressible Reynolds Averaged Navier-Stokes (RANS) turbulence model has been opted with the finite-rate/eddy-dissipation reaction model. K-ε two equation turbulence model has been selected to reach up to reasonable accuracy. Validation of the present work has been done with the help of both non-reacting and reacting type data from open literature. To choose the appropriate meshing of the computational model three different types of mesh elements, that is, coarse, medium and fine has been analysed and also grid independence analysis is performed. The present article objective is to get optimum boundary condition by changing the incoming air temperature and pressure at constant Mach number to connect the bridge between incoming air temperature and pressure to the change in velocity throughout the combustion chamber. The detailed understanding and explanation have been done by varying the temperature range of incoming air because of its major impact on combustion performance. Nonetheless, a small variation of air pressure will also discuss to observe the parameters which majorly influence while doing performance analysis. At the end the Optimum boundary condition for the present computation work is observed to be at 833 K temperature with 115 299 Pa pressure.

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“…Currently, the research process of scramjets is mainly focused on liquid fuel, such as kerosene and liquid hydrogen [8,11,[14][15][16][17][18]. However, compared with the liquid fuel scramjets, solid fuel scramjets have the same advantages as traditional solid fuel engines, such as simple structure, high energy density, good maneuverability, and long storage time, etc.…”

Section: Introductionmentioning

confidence: 99%

Numerical Study on the Solid Fuel Rocket Scramjet Combustor with Cavity

Xia

et al. 2019

Energies

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Scramjet based on solid propellant is a good supplement for the power device of future hypersonic vehicles. A new scramjet combustor configuration using solid fuel, namely, the solid fuel rocket scramjet (SFRSCRJ) combustor is proposed. The numerical study was conducted to simulate a flight environment of Mach 6 at a 25 km altitude. Three-dimensional Reynolds-averaged Navier–Stokes equations coupled with shear stress transport (SST) k − ω turbulence model are used to analyze the effects of the cavity and its position on the combustor. The feasibility of the SFRSCRJ combustor with cavity is demonstrated based on the validation of the numerical method. Results show that the scramjet combustor configuration with a backward-facing step can resist high pressure generated by the combustion in the supersonic combustor. The total combustion efficiency of the SFRSCRJ combustor mainly depends on the combustion of particles in the fuel-rich gas. A proper combustion organization can promote particle combustion and improve the total combustion efficiency. Among the four configurations considered, the combustion efficiency of the mid-cavity configuration is the highest, up to about 70%. Therefore, the cavity can effectively increase the combustion efficiency of the SFRSCRJ combustor.

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Combustion characteristics of hydrogen and cracked kerosene in a DLR scramjet combustor using hybrid RANS/LES method

Cited by 30 publications

References 23 publications

Effects of cavity parameters on flame flashback phenomenon in a supersonic crossflow with a cavity flameholder

Effects of cavity parameters on flame flashback phenomenon in a supersonic crossflow with a cavity flameholder

Impact of parametric variation on combustion characteristics of hydrogen‐fueled strut based scramjet combustor at supersonic speed

Numerical Study on the Solid Fuel Rocket Scramjet Combustor with Cavity

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