Investigation of Geometric Characteristics on the Non-Reaction Supersonic Flow inside the Channel with the Presence of Cavities

Document Type : Research Article

Authors

1 PHD Student, Malek Ashtar Uni.

2 Aerospace Department, Associated Professor

3 Mech. Dept., MUT, Iran

Abstract

In the present work, the flow inside a channel with a cavity is investigated as a Scramjet combustion chamber. For this aim, the parameters such as L/D (cavity length to cavity depth), H/D (channel height to cavity depth), and varied Mach numbers are studied in the supersonic flow to investigate the effect of geometric parameters on channel flow in non- reacting conditions. In this work, vorticity is used as a mixing parameter. Two-dimensional Navier-Stokes equations are used to solve the steady-state flow. The density based method and standard k-ε Model are employed for numerical simulation. The results show that vorticity of boundary layer and thus mixing in flow is increased with growing of L/D, Mach number and having sweep angle for the cavity. Geometries with larger H/D performed better than other geometries in terms of generating vorticity and reducing Total pressure loss. Although the H/D = 1 ratio has a higher recirculation than others, it will not be reliable for all supersonic flow because of its considerable total pressure loss and the survival of the oblique shock in some conditions.

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Main Subjects

References

[1] A. Ben Yakar, R.K. Hanson, Cavity Flame-Holders for Ignition and Flame Stabilization in Scramjets: An Overview, Journal of Propulsion and Power, 17(4) (2001) 869-877.
[2] S. Jeyakumar, S.M. Assis, K. Jayaraman, effect of Axisymmetric aft wall angle cavity in supersonic flowfield, International Journal of Turbo and Jet Engines, 35(1) (2018) 29-34.
[3] K.N. Jayachandran, N. Nithin, S. Dhinesh, A.M. Irfan, D.T. Murugan, Performance Analysis of Double Cavity Based Scramjet Combustion at Mach 2 using CFD, International Journal of Emerging Technology and Advanced Engineering, 4(3) (2014) 110-119.
[4] M.R. Gruber, R.A. Baurle, T. Mathur, K.Y. Hsu, Fundamental studies of cavity-based flameholder concepts for supersonic combustors, Journal of Propulsion and Power, 17(1) (2001) 146-153.
[5] V. Sridhar, S.L. Gai, H. Kleine, A Numerical Investigation of Supersonic Cavity Flow At Mach 2, in:  18th Australasian Fluid Mechanics Conference, Launceston, Australia, 2012.
[6] K.M. Kim, S.W. Baek, C.Y. Han, Numerical study on supersonic combustion with cavity-based fuel injection, International Journal of Heat and Mass Transfer, 47 (2004) 271-286.
[7] M. Dharavath, P. Manna, D. Chakraborty, Numerical Investigation of Hydrogen-fuelled Scramjet combustor with cavity Flame Holder, Defence Science Journal, 64(5) (2014) 417-425.
[8] W. Huang, Z.g. Wang, M. Pourkashanian, L. Ma, D.B. Ingham, S.B. Luo, J. Liu, Hydrogen fuelled scramjet combustor—the impact of fuel injection, in:  Fuel Injection, Sciyo, 2010.
[9] S.B. Luo, W. Huang, J. Liu, Z.G. Wang, Drag force investigation of cavities with different geometric configurations in supersonic flow, Science China Technological Science, 54(5) (2011) 1345-1350.
[10] W. Huang, Z.G. Wang, L. Yan, W.D. Liu, Numerical validation and parametric investigation on the cold flow field of a typical cavity-based scramjet combustor, Journal of Acta Astrnautica, 80(1) (2012) 132-140.
[11] W. Huang, M. Pourkashanian, L. Ma, D.B. Ingham, S.B. Luo, Z.g. Wang, Effect of geometric parameters on the drag of the cavity flameholder based on the variance analysis method, Aerospace Science and Technology, 21 (2012) 24-30.
[12] P. Hashemi, M. Dahghan Manshadi, A. Mostofizadeh, Role of the vortical structures in combustion of jet in cross flow at inlet of supersonic nozzle, Aerospace propulsion, 1(2) (2014) 11-22 (in persian).
[13] M. Zahedzadeh, F. Ommi, Numerical Study of Staged Transverse Injection of Sonic Jets into Supersonic Crossflows behind a Step, Journal of Modeling in Engineering, 17(56) (2019) 281-291 (in persian).
[14] M. Lahijani, S. Emami Koopaei, Effect of the number of cavity flame-holders on combustion efficiency and pressure recovery factor in a supersonic combustion chamber, Fuel and Combustion, 13(1) (2020 ) 98-117 (in persian).
[15] F. Xing, M.M. Zhao, S. Zhang, Simulations of a Cavity Based Two-Dimensional Scramjet Model, in:  18th Australasian Fluid Mechanics Conference, Launceston, Australia, 2012.
[16] D. Zhang, Q. Wang, Numerical Simulation of Supersonic Combustor with Innovative Cavity, International Conference on Advances in Computational Modeling and Simulation, Procedia Engineering, 31 (2012) 708-712.
[17] M.F. Khan, R. Yadav, Z.A. Quadri, S.F. Anwar, Numerical Study of the Cavity Geometry on Supersonic Combustion with Transverse Fuel Injection, in:  Numerical study of cavity geometry on fluid Mechanics and Fluid power, 2017, pp. 1509-1518.
[18] W.L. Lui, L. Zhu, Y.Y. Qi, J.R. Ge, F. Luo, H.R. Zou, M. Wei, T.C. Jen, Effects of injection pressure variation on mixing in a cold supersonic combustor with kerosene fuel, Acta Astronautica, 139 (2017) 67-76.
[19] W. Yang, J. Fu, X. Ma, R. Xing, Numerical Study on Configuration of Scramjet Combustor, in:  IOP Conf. Materials Science and Engineering, 2018.
[20] Z. Cai, M. Sun, Z. Wang, X. Bai, Effect of cavity geometry on fuel transport and mixing processes inascramjet combustor, ournal of Aerospace Science and Technology, 80 (2018) 309-314.
[21] L. Suneetha, P. Randive, K.M. Pandey, Numerical investigation on mixing behavior of fuels inreacting and non-reacting flow condition of a cavity-strut based scramjet combustor, International Journal of Hydrogen Energy, 44(31) (2019) 16718-16734.
[22] S. Jeyakumar, S.M. Assis, K.N. Jayachandran, Experimental Study on the characteristics of axisymmetric cavity actuated supersonic flow, Journl of Aerospace Engineering,SAGE, 0(0) (2016) 1-8.
[23] S. Jeyakumar, S.M. Assis, K. Jayaraman, Effect of Axisymmetric Aft Wall Angle Cavity in Supersonic Flow Field, International Journal of Turbo and Jet Engines, 35(1) (2016).
[24] S. Etheridge, J.G. Lee, C. Carter, M. Hagenmaier, R. Milligan, Effect of flow distortion on fuel/air mixing and combustion in an upstream-fueled cavity flameholder for a supersonic combustor, Experimental Thermal and Fluid Science, 88 (2017) 461-471.
[25] Z. Cai, J. Zhu, M. Sun, Z. Wang, Effect of cavity fueling schemes on the laser-induced plasma ignition process in a scramjet combustor, Aerospace Science and Technology, 78 (2018) 197–204.
[26] Y. Wang, Z. Wang, M. Sun, H. Wang, Z. Cai, Effects of fueling distance on combustion stabilization modes in a cavity- based scramjet combustor, Acta Astronautica, 155 (2019) 23-32.
[27] G. Choubey, K. Pandey, Effect of variation of inlet boundary conditions on the combustion flow-field of a typical double cavity scramjet combustor, International Journal of Hydrogen Energy, 43 (2018/03/01).
[28] O. Chakraborty, D. Sharma, K.O. Reddy, K.M. Pandey, CFD Analysis of Cavity Based Combustion of Hydrogen at Mach Number 1.4, Current Trends in Technology and Sciences, 1(3) (2012).
[29] D.C. Wilcox, Turbulence Modeling for CFD, DCW Industries, 2002.
[30] L. Abu-Farah, O. Haidn, H.P. Kau, Numerical simulations of single and multi-staged injection of H2 in a supersonic scramjet combustor, Propulsion and Power Research, 3(4) (2014) 175-186.
Amirkabir Journal of Mechanical Engineering
Volume 53, Issue 11
February 2022
Pages 5409-5428

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