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Abstract: An efficient mixing process is very important for the engineering implementation of an airbreathing propulsion system. The air and injectant should be mixed sufficiently before entering the combustor. Two new wall-mounted cavity configurations were proposed to enhance the mixing process in a conventional transverse injection flow field. Their flow field properties were compared with those of a system with only transverse injection ports. Grid independency analysis was used to choose a suitable grid scale, and the mixing efficiencies at four cross-sectional planes (namely x=20, 40, 60, and 80 mm, which are just downstream of the jet orifice) were compared for the configurations considered in this study. The results showed that hydrogen penetrated deeper when a cavity was mounted upstream of the transverse injection ports. This is beneficial to the mixing process in supersonic flows. The mixing efficiency of the configuration with the wall-mounted cavity was better than that of the conventional physical model, and the mixing efficiency of the proposed novel physical model I (98.71% at x=20 mm) was the highest of all. In the case with only transverse injection ports, the vortex was broken up by the strong interaction between the shear layer over the cavity and the jet.

The authors propose to study two newly wall-mounted cavity configurations to enhance the mixing process in supersonic mixing, as scramjet engines combustors. By extending the experimental works of T. Handa & coworkers to further investigate the mixing properties of two new cavity configurations located ahead the injectors. A numerical study is showed to compare three configurations: conventional, novel I and novel II. The work is innovative and interesting.

壁面凹腔诱导的超声速混合增强机制研究

[1]Alexander, D.C., Sislian, J.P., Parent, B., 2006. Hypervelocity fuel/air mixing in mixed-compression inlets of shcramejts. AIAA Journal, 44(10):2145-2155.

[2]Das, R., Kim, J.S., Kim, H.D., 2015. Supersonic cavity based combustion with kerosene/hydrogen fuel. Journal of Thermal Science, 24(2):164-172.

[3]Fluent Inc., 2006. Fluent 6.3 User’s Guide. Fluent Inc., Lebanon, NH, USA.

[4]Freeborn, A.B., King, P.I., Gruber, M.R., 2009. Swept-leading-edge pylon effects on a scramjet pylon-cavity flameholder flowfield. Journal of Propulsion and Power, 25(3):571-582.

[5]Grady, N.R., Pitz, R.W., Carter, C.D., et al., 2012. Supersonic flow over a ramped-wall cavity flame holder with an upstream strut. Journal of Propulsion and Power, 28(5):982-990.

[6]Gruber, M.R., Carter, C.D., Montes, D.R., et al., 2008. Experimental studies of pylon-aided fuel injection into a supersonic crossflow. Journal of Propulsion and Power, 24(3):460-470.

[7]Gruenig, C., Avrashkov, V., Mayinger, F., 2000. Fuel injection into a supersonic airflow by means of pylons. Journal of Propulsion and Power, 16(1):29-34.

[8]Handa, T., Nakano, A., Tanigawa, K., et al., 2014. Supersonic mixing enhanced by cavity-induced three-dimensional oscillatory flow. Experiments in Fluids, 55:1711.

[9]Hsu, K.Y., Carter, C.D., Gruber, M.R., et al., 2010. Experimental study of cavity-strut combustion in supersonic flow. Journal of Propulsion and Power, 26(6):1237-1246.

[10]Huang, W., 2014. Design exploration of three-dimensional transverse jet in a supersonic crossflow based on data mining and multi-objective design optimization approaches. International Journal of Hydrogen Energy, 39(8):3914-3925.

[11]Huang, W., 2015. Effect of jet-to-crossflow pressure ratio arrangement on turbulent mixing in a flowpath with square staged injectors. Fuel, 144:164-170.

[12]Huang, W., Yan, L., 2013. Progress in research on mixing techniques for transverse injection flow fields in supersonic crossflows. Journal of Zhejiang University-SCIENCE A (Applied Physics & Engineering), 14(8):554-564.

[13]Huang, W., Pourkashanian, M., Ma, L., et al., 2011a. Investigation on the flameholding mechanisms in supersonic flows: backward-facing step and cavity flameholder. Journal of Visualization, 14(1):63-74.

[14]Huang, W., Wang, Z.G., Jin, L., et al., 2011b. Effect of cavity location on combustion flow field of integrated hypersonic vehicle in near space. Journal of Visualization, 14(4):339-351.

[15]Huang, W., Wang, Z.G., Luo, S.B., et al., 2011c. Parametric effects on the combustion flow field of a typical strut-based scramjet combustor. Chinese Science Bulletin, 56(35):3871-3877.

[16]Huang, W., Pourkashanian, M., Ma, L., et al., 2012a. Effect of geometric parameters on the drag of the cavity flameholder based on the variance analysis method. Aerospace Science and Technology, 21(1):24-30.

[17]Huang, W., Liu, W.D., Li, S.B., et al., 2012b. Influences of the turbulence model and the slot width on the transverse slot injection flow field in supersonic flows. Acta Astronautica, 73:1-9.

[18]Huang, W., Ma, L., Pourkashanian, M., et al., 2012c. Parametric effects in a scramjet engine on the interaction between the air stream and the injection. Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering, 226(3):294-309.

[19]Huang, W., Liu, J., Yan, L., et al., 2013a. Multiobjective design optimization of the performance for the cavity flameholder in supersonic flows. Aerospace Science and Technology, 30(1):246-254.

[20]Huang, W., Li, S.B., Yan, L., et al., 2013b. Performance evaluation and parametric analysis on cantilevered ramp injector in supersonic flows. Acta Astronautica, 84:141-152.

[21]Huang, W., Jin, L., Yan, L., et al., 2014a. Influence of jet-to-crossflow pressure ratio on nonreacting and reacting processes in a scramjet combustor with backward-facing steps. International Journal of Hydrogen Energy, 39(36):21242-21250.

[22]Huang, W., Wang, Z.G., Yan, L., et al., 2014b. Variation of inlet boundary conditions on the combustion characteristics of a typical cavity-base scramjet combustor. Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering, 228(4):627-638.

[23]Kim, K.M., Baek, S.W., Han, C.Y., 2004. Numerical study on supersonic combustion with cavity-based fuel injection. International Journal of Heat and Mass Transfer, 47(2):271-286.

[24]Lee, S.H., 2012. Mixing augmentation with cooled pylon injection in a scramjet combustor. Journal of Propulsion and Power, 28(3):477-485.

[25]Lee, S.H., Mitani, T., 2003. Mixing augmentation of transverse injection in scramjet combustor. Journal of Propulsion and Power, 19(1):115-124.

[26]Pohlman, M.R., Greendyke, R.B., 2013. Parametric analysis of pylon-aided fuel injection in scramjet engines. Journal of Engineering for Gas Turbines and Power, 135(2):024501.

[27]Pudsey, A.S., Boyce, R.R., 2010. Numerical investigation of transverse jets through multiport injector arrays in supersonic crossflow. Journal of Propulsion and Power, 26(6):1225-1236.

[28]Segal, C., 2009. The Scramjet Engine: Processes and Characteristics. Cambridge University Press, UK.

[29]Smirnov, N.N., Nikitin, V.F., 2014. Modeling and simulation of hydrogen combustion in engines. International Journal of Hydrogen Energy, 39(2):1122-1136.

[30]Smirnov, N.N., Betelin, V.B., Shagaliev, R.M., et al., 2014. Hydrogen fuel rocket engines simulation using LOGOS code. International Journal of Hydrogen Energy, 39(20):10748-10756.

[31]Sujith, S., Muruganandam, T.M., Kurian, J., 2013. Effect of trailing ramp angles in strut-based injection in supersonic flow. Journal of Propulsion and Power, 29(1):66-78.

[32]Takahashi, H., Tu, Q., Segal, C., 2010. Effects of pylon-aided fuel injection on mixing in a supersonic flowfield. Journal of Propulsion and Power, 26(5):1092-1101.

[33]Vergine, F., Crisanti, M., Maddalena, L., 2015. Supersonic combustion of pylon-injected hydrogen in high-enthalpy flow with imposed vortex dynamics. Journal of Propulsion and Power, 31(1):89-103.

[34]Vinogradov, V.A., Shikhman, Y.M., Segal, C., 2007. A review of fuel pre-injection in supersonic, chemically reacting flows. Applied Mechanics Reviews, 60(4):139-148.

[35]Yu, K.H., Schadow, K.C., 1994. Cavity-actuated supersonic mixing and combustion control. Combustion and Flame, 99(2):295-301.

[36]Zare-Behtash, H., Lo, K.H., Kontis, K., et al., 2015. Transverse jet-cavity interactions with the influence of an impinging shock. International Journal of Heat and Fluid Flow, 53:146-155.