Abstract
A numerical study on mixing of hydrogen injected into a supersonic air stream has been performed by solving two-dimensional full Navier-Stokes equations. An explicit Harten-Yee Non-MUSCL Modified-flux-type TVD scheme has been used to solve the system of equations, and a zero-equation algebraic turbulence model to calculate the eddy viscosity coefficient. The main objectives of this study are to increase the mixing efficiency and flame holding capability of a supersonic combustor. The performance of combustor has been investigated by varying the hydrogen injection angle made with the direction of air stream considering anti-clockwise direction as positive. The injector position from left boundary, backward-facing step height and the inlet width of air stream are kept constant. The results show that upstream of injector the mixing is dominated by recirculation and in downstream the mixing is dominated by mass concentration of hydrogen. Upstream recirculation is dominant for injecting angle 60° and 90°. Incorporating the various effects, perpendicular injection shows the maximum mixing efficiency and its large upstream recirculation region has a good flame holding capability.
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References
Brown, G L, Roshko, A. On Density Effects and Large Structure in Turbulent Mixing Layer. J. Fluid Mechanics, 1974, 64(4): 575–816
Papamoschou, D, Roshko, A. Observation of Supersonic Free Shear Layers. AIAA Paper 86-0162, 1986
Rogers, R C. A Study of the Mixing of Hydrogen Injected Normal to a Supersonic Airstream. NASA TN D-6114, 1971
Kraemer, G O, Tiwari, S N. Interaction of Two-Dimensional Transverse Jet with a Supersonic Mainstream. NASA CR 175446, 1983
Holdeman, J D, Walker, R E. Mixing of a Row of Jets with a Confined Crossflow, AIAA Journal, 1977, 5(2)
Thayer III, W J, Corlett, R C. Gas Dynamic and Transport Phenomena in the Two-Dimensional Jet Interaction Flowfield. AIAA Journal, 1972, 10
Heister, S D, Nguyen, T T, Karagozian, A R. Modeling of Liquid Jets Injected Transversely into a Supersonic Crossflow. AIAA Journal, 1989, 27(12): 1727–1734
Ali, M, Fujiwara, T, Leblanc, J E. Influence of Main Flow Configuration on Mixing and Flameholding in Transverse Injection into Supersonic Airstream. Int. Journal Engineering Science, 2000, 38: 1161–1180
Ali, M, Islam, A K M S. Effect of Mainflow Inlet Width on Penetration and Mixing of Hydrogen in Scramjet Combustor. In: Proceedings of the Eighth Asian Congress of Fluid Mechanics, Shenzhen, China. 1999. 647–650
Weidner, E H, Drummond, J P. A Parametric Study of Staged Fuel Injector Configurations for Scramjet Applications. AIAA Paper 81-11468, 1981
Rausch, V L, McClinton, C R, Hicks, J W. Scramjet Breath New Life into Hypersonics. Aerospace America, 1997, 40–46
Moss, J N. Reacting Viscous-Shock-Layer Solutions with Multicomponent Diffusion and Mass Injection. NASA TR-411, 1974
White, F M. Viscous Fluid Flow. McGraw-Hill, New York, 1974
Reid, R C, Sherwood, T K. The Properties of Gases and Liquids. Second Edition. McGraw-Hill, New York, 1966, 520–543.
Baldwin, B S, Lomax, H. Thin Layer Approximation and Algebraic Model for Separated Turbulent Flows. AIAA Paper 78-257, 1978
Yee, H C. A Class of High-Resolution Explicit and Implicit Shock Capturing Methods. NASA, TM 101088, 1989
Yee, H C. Upwind and Symmetric Shock-Capturing Schemes. NASA TM 89464, 1990
Tabejamaat, S JU Y, Niioka, T. Numerical Simulation of Secondary Combustion of Hydrogen Injected from Preburner into Supersonic Airflow. AIAA Journal, 1997, 35(9)
Yokota, K, Kaji, S. The Three-Dimensional Supersonic Flow and Mixing Fields with a Perpendicular Air Injection from a Finite Length Slit. Trans. Japan Soc. Aero. Space Sci., 1996, 39(124): 173–183
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Ahmed, S., Ali, M. & Islam, A.K.M.S. The effect of injection angle on mixing and flame holding in supersonic combustor. J. of Therm. Sci. 11, 80–91 (2002). https://doi.org/10.1007/s11630-002-0026-0
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DOI: https://doi.org/10.1007/s11630-002-0026-0