The conventional method for cavity analysis is solving two-dimensional equations. The two-dimensional implicit and density-based Reynolds averaged Navier–Stokes equations and the two-equation standard k–ε turbulence model have been employed to numerically simulate the cold flow field in a single-cavity flame-holding configuration of a supersonic combustor. The cross section of the combustor is assumed to be rectangular. The supersonic inlet is supposed for the steady and unsteady flow conditions along with normal directions to the inlet. For the validation purpose, the numerical results are compared with those of the experimental data available in the current literature. It is quite well-known that the cavity in supersonic combustors helps to separate the fuel from the wall configuration while improving the mixing process in supersonic flows. However, the selection of the most efficient depth for the cavity is crucial in obtaining optimum conditions. In the present research work, the role of the cavity length-to-height (L/D) ratio, the channel height-to-cavity height (H/D) ratio and Mach number are studied numerically. The obtained results indicate that the wall static pressure profiles of validation case predicted by the numerical approaches are well in agreement with those of the experimental data. Also, H/D = 2 was found to be the best choice for the combustion chamber height relative to the cavity depth. The designed geometry is modeled in a commercial software using two-dimensional density-based energy equations while the turbulent characteristics are modeled using standard k-ε turbulence model.
This is a preview of subscription content, access via your institution.
Buy single article
Instant access to the full article PDF.
Tax calculation will be finalised during checkout.
Subscribe to journal
Immediate online access to all issues from 2019. Subscription will auto renew annually.
Tax calculation will be finalised during checkout.
Downstream step height
Upstream step height
Turbulent kinetic energy
Height of combustor
Combustor height-to-cavity depth ratio
Cavity length-to-depth ratio
Non-dimensional distance comprises, the distance upstream of the cavity, forward face from separation corner, the cavity floor and the cavity rear face
Li J, Zhang L, Choi J, Yang V, Lin K (2014) Ignition transients in a scramjet engine with air throttling, part 1: nonreacting flow. J Propuls Power 30(2):438–448
Huang W, Wang Z, Yan L, Liu W (2012) Numerical validation and parametric investigation on the cold flow field of a typical cavity-based scramjet combustor. Acta Astrnautica 80(1):132–140
Huang W, Liu J, Yan L, Jin L (2013) Multiobjective design optimization of the performance for the cavity flameholder in supersonic flows. Aerosp Sci Technol 30:246–254
Gao P, Chang X, Gao S, Zhu J (2012) the influence of supersonic combustion when the cavity parameters changed on the chamber wall. Adv Mater Res 468:2620–2623
Sridhar V, Gai SL, Kleine H (2012) A numerical investigation of supersonic cavity flow at Mach 2. In: 18th Australasian Fluid Mechanics Conference, Launceston, Australia, 3–7 December 2012.
Zhang J, Morishita E, Okunuki T, Itoh H (2005) experimental investigation on the mechanism of flow type changes in supersonic cavity flows. Trans Jpn Soc Aeron Space Sci 45(149):170–179
Kizhakkedathu J, Nithin N, Dhinesh S, Irfan A, Murugan DT (2014) Performance analysis of double cavity based scramjet combustion at mach 2 using CFD. Int J Emerg Technol Adv Eng 4(3):110–119
Dharavath M, Manna P, Chakrabort D (2014) Numerical Investigation of Hydrogen-fuelled Scramjet combustor with cavity Flame Holder. Def Sci J 64(5):417–425
Ben-Yakar A, Hanson R (2001) Cavity flame-holders for ignition and flame stabilization in scramjets: an overview. J Propuls Power 17(4):869–877
Gruber M, Baurle R, Hsu K, Mathur T (2001) Fundamental studies of cavity-based flame- holder concepts for supersonic combustors. J Propuls Power 17(1):146–153
Yu G, Li J, Zhang X, Chen L, Han B, Sung C (2002) Experimental investigation on flame-holding mechanism and combustion performance in hydrogen fuelled supersonic combustor. Combust Sci Technol 174:1–27
Kim K, Baek S, Han C (2004) Numerical study on supersonic combustion with cavity-based fuel injection. Int J Heat Mass Transf 47:271–286
Huang W, Luo S, Liu J, Wang Z (2010) Effect of cavity flame holder configuration on combustion flow field performance of integrated hypersonic vehicle. Sci China Technol Sci 53:2725–2733
Huang W, Wang Z, Zhen-guo, Pourkashanian M, Ma L, Ingham DB, Luo S, Liu J (2010) Hydrogen fuelled scramjet combustor—the impact of fuel injection. In: Fuel injection. IntechOpen, pp 167–182
Luo S, Huang W, Liu J, Wang Z (2011) Drag force investigation of cavities with different geometric configurations in supersonic flow. Sci China Technol Sci 54:1345–1350
Huang W, Pourkashanian M, Ma L, Ingham D, Luo S, Wang Z (2011) Effect of geometric parameters on the drag of the cavity flameholder based on the variance analysis method. Aerosp Sci Technol 21:24–30
Pandey K, Kalita P, Barman K, Rajkhowa A, Saikia S (2011) CFD analysis of wall injection with large sized cavity based scramjet combustion at mach 2. Int J Eng Technol 3(2):122–129
Xing F, Zhao M, Zhang S (2012) Simulations of a cavity based two-dimensional scramjet model. In: 18th Australasian Fluid Mechanics Conference. Launceston, Australia
Zhang D, Wang Q (2012) Numerical simulation of supersonic combustor with innovative cavity. Procedia Eng 31:708–712
Pandey K (2012) CFD analysis of cavity based combustion of hydrogen at mach number 1.4. Curr Trends Technol Sci 1(3):126–133
Yanhui Z, Jianhan L, Yuxin Z (2016) Non-reacting flow visualization of supersonic combustor based on cavity and cavity–strut flameholder. Acta Astronaut 121:282–291
Suppandipillai J, Assis S, Kandasamy J (2016) Experimental study on the characteristics of axisymmetric cavity actuated supersonic flow. In: Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering, 231
Suppandipillai J, Assis S, Kandasamy J (2016) Effect of axisymmetric aft wall angle cavity in supersonic flow field. Int J Turbo Jet-Engines 35(1):29–34
Khan MF, Yadav R, Quadri Z, Anwar S (2017) Numerical study of the cavity geometry on supersonic combustion with transverse fuel injection. In: Lecture Notes in Mechanical Engineering, pp. 1509–1518
Etheridge S, Lee J, Carter C, Hagenmaier M, Milligan R (2017) Effect of flow distortion on fuel/air mixing and combustion in an upstream-fueled cavity flameholder for a supersonic combustor. Exp Thermal Fluid Sci 88:461–471
Liu W, Zhu L, Qi Y, Ge J, Luo F, Zou H, Wei M, Jen T (2017) Effects of injection pressure variation on mixing in a cold supersonic combustor with kerosene fuel. Acta Astronaut 139:67–76
Shaohua Z, Xu X, Yang Q (2018) Application of the vortex effects induced by the trailing wedge to improve the mixing and combustion in the dual- strut scramjet. Appl Therm Eng 140:604–614
Sathiyamoorthy K, Danish T, Srinivas J, Pulumathi M (2018) Experimental investigation of supersonic combustion in a strut-cavity based combustor. Acta Astronaut 148:285–293
Yang W, Fu ,Ma X, Xing R (2018) Numerical study on configuration of scramjet combustor. In: IOP Conference Series: Materials Science and Engineering, 408
Cai Z, Sun M, Wang Z, Bai X (2018) Effect of cavity geometry on fuel transport and mixing processes inascramjet combustor. Aerosp Sci Technol 80:309–314
Cai Z, Zhu J, Sun M, Wang Z (2018) Effect of cavity fueling schemes on the laser-induced plasma ignition process in a scramjet combustor. Aerosp Sci Technol 78:197–204
Lakka S, Randive P, Pandey K (2019) Numerical investigation on mixing behavior of fuels inreacting and non-reacting flow condition of a cavity-strut based scramjet combustor. Int J Hydrog Energy 44:16718–16734
Zhao G, Sun M, Wu J, Cui X, Wang H (2019) Investigation of flame flashback phenomenon in a supersonic crossflow with ethylene injection upstream of cavity flameholder. Aerosp Sci Technol 87:190–206
Wang Y, Wang Z, Sun M, Wang H, Cai Z (2018) Effects of fueling distance on combustion stabilization modes in a cavity- based scramjet combustor. Acta Astronaut 155:23–32
Huang W, Wang Z, Pourkashanian M, Ma L, Ingham D, Luo S, Lei J, Liu J (2011) Numerical investigation on the shock wave transition in a three- dimensional scramjet isolator. Acta Astronaut 68:1669–1675
Huang W, Ma L, Wang Z, Pourkashanian M, Ingham D, Luo S, Lei J (2011) A parametric study on the aerodynamic characteristics of a hypersonic wave rider vehicle. Acta Astronaut 69:135–140
Launder B, Spalding DB (1974) The numerical computation of turbulent flows. Comput Methods Appl Mech Eng 3(2):456–460
Zingg D, Godin P (2009) A perspective on turbulence models for aerodynamic flows. Int J Comput Fluid Dyn 23:327–335
Kim J, Kim H, Setoguchi T, Matsuo S (2008) Computational study on the critical nozzle flow of high-pressure hydrogen gas. J Propuls Power 24:715–721
Huang W, Li M, Ding F, Liu J (2016) Supersonic mixing augmentation mechanism induced by a wall-mounted cavity configuration. J Zhejiang Univ Sci A Appl Phys Eng 17(1):45–53
Pudsey A, Boyce R (2010) Numerical investigation of transverse jets through multiport injector arrays in supersonic crossflow. J Propuls Power 26(6):225–1236
Springer Nature remains neutral with regard to jurisdictional claims in published maps and institutional affiliations.
Technical Editor: André Cavalieri.
About this article
Cite this article
Dashti Rahmat Abadi, V., Agha Seyed Mirzabozorg, M. & Kheradmand, S. Enhancing mixing features in supersonic flow through geometric correction of the cavity depth relative to the height of the combustion chamber. J Braz. Soc. Mech. Sci. Eng. 43, 129 (2021). https://doi.org/10.1007/s40430-021-02832-w
- Supersonic combustion
- Computational fluid dynamics (CFD)