Abstract
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-ω 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.
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Voland R T, Huebner L D, McClinton C R. X-43A hypersonic vehicle technology development. Acta Astronaut, 2006, 59: 181–191
Huang W, Pourkashanian M, Ma L, et al. Investigation on the flameholding mechanisms in supersonic flows: Backward-facing step and cavity flameholder. J Visual, 2011, 14: 63–74
Huang W, Luo S B, Wang Z G. Key techniques and prospect of near-space hypersonic vehicle (in Chinese). J Astronaut, 2010, 31: 1259–1265
Huang W, Qin H, Luo S B, et al. Research status of key techniques for shock-induced combustion ramjet (shcramjet). Sci China Tech Sci, 2010, 53: 220–226
Gerlinger P, Stoll P, Kindler M, et al. Numerical investigation of mixing and combustion enhancement in supersonic combustors by strut induced streamwise vorticity. Aerosp Sci Technol, 2008, 12: 159–168
Zou J F, Zheng Y, Liu O Z. Simulation of turbulent combustion in DLR Scramjet. J Zhejiang Univ-Sc A, 2007, 8: 1053–1058
Oevermann M. Numerical investigation of turbulent hydrogen combustion in a SCRAMJET using flamelet modeling. Aerosp Sci Technol, 2000, 4: 463–480
Kumaran K, Behera P R, Babu V. Numerical investigation of the supersonic combustion of kerosene in a strut-based combustor. J Propul Power, 2010, 26: 1084–1091
Genin F, Menon S. Simulation of turbulent mixing behind a strut injector in supersonic flow. AIAA J, 2010, 48: 526–539
Berglund M, Fureby C. LES of supersonic combustion in a scramjet engine model. P Combust Inst, 2007, 31: 2497–2504
Berglund M, Fedina E, Fureby C, et al. Finite rate chemistry large-eddy simulation of self-ignition in a supersonic combustion ramjet. AIAA J, 2010, 48: 540–550
Luo S B, Huang W, Pourkashanian M, et al. Investigation of turbulent models for the flow field from a typical strut-based scramjet combustor. Proceedings of ASME Turbo Expo 2011, Vancouver, Canada, 2011
Li J G, Yu G, Zhang Y, et al. Experimental studies on self-ignition of hydrogen/air supersonic combustion. J Propul Power, 1997, 13: 538–542
Engman E. Numerical simulation of scramjet combustion. Master’s Degree. Sweden: Lulea University of Technology, 2008
Huang W, Luo S B, Liu J, et al. Effect of cavity flame holder configuration on combustion flow field performance of integrated hypersonic vehicle. Sci China Tech Sci, 2010, 53: 2725–2733
Huang W, Luo S B, Pourkashanian M, et al. Numerical simulations of typical hydrogen fueled scramjet combustor with a cavity flameholder. The 2010 International Conference of Mechanical Engineering, London, UK, 2010
Gu H B, Chen L H, Chang X Y. Experimental investigation on the cavity-based scramjet model. Chinese Sci Bull, 2009, 54: 2794–2799
Kim K M, Baek S W, Han C Y. Numerical study on supersonic combustion with cavity-based fuel injection. Int J Heat Mass Tran, 2004, 47: 271–286
Takahashi S, Yamano G, Wakai K, et al. Self-ignition and transition to flame-holding in a rectangular scramjet combustor with a backward step. P Combust Inst, 2000, 28: 705–712
Halupovich Y, Natan B, Rom J. Numerical solution of the turbulent supersonic flow over a backward facing step. Fluid Dyn Res, 1999, 24: 251–273
Luo S B, Huang W, Lei J, et al. Drag force characteristic of a typical dual-mode scramjet combustor. The 2010 International Conference on Mechanical and Aerospace Engineering (CMAE 2010), Chengdu, China, 2010
Zhao Z, Song W Y, Xiao Y L, et al. An experimental investigation of the cold flowfield in a model scramjet combustor. P I Mech Eng G-J Aer, 2009, 223: 425–431
Yu G, Li J G, Zhang X Y, et al. Experimental investigation on flameholding mechanism and combustion performance in hydrogen-fueled supersonic combustors. Combust Sci Technol, 2002, 174: 1–27
Hsu K Y, Carter C D, Gruber M R, et al. Experimental study of cavity-strut combustion in supersonic flow. J Propul Power, 2010, 26: 1237–1246
Huang W, Pourkashanian M, Wang Z G, et al. Overview of fuel injection techniques for scramjet engines. Proceedings of ASME Turbo Expo 2011, Vancouver, Canada, 2011
Zingg D W, Godin P. A perspective on turbulence models for aerodynamic flows. Int J Comput Fluid D, 2009, 23: 327–335
Rogers R C, Chinitz W. On the use of hydrogen-air combustion model in the calculation of turbulent reacting flows. AIAA Paper 1982-0112, 1982
Huang W, Wang Z G, Pourkashanian M, et al. Numerical investigation on the shock wave transition in a three-dimensional scramjet isolator. Acta Astronaut, 2011, 68: 1669–1675
Tohru M, Toshinori K. Flame structures and combustion efficiency computed for a Mach 6 scramjet engine. Combust Flame, 2005, 142: 187–196
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Huang, W., Wang, Z., Luo, S. et al. Parametric effects on the combustion flow field of a typical strut-based scramjet combustor. Chin. Sci. Bull. 56, 3871–3877 (2011). https://doi.org/10.1007/s11434-011-4823-2
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DOI: https://doi.org/10.1007/s11434-011-4823-2