Abstract
The combustion performance of hydrogen fuel in a scramjet combustor has been a popular focus for scholars all over the world. In this study, the influence of the jet-to-crossflow pressure ratio on combustion performance in a scramjet combustor was investigated numerically, and the influence of a wall-mounted cavity was evaluated. The simulations were conducted using the Reynolds-averaged Navier-Stokes (RANS) equations coupled with the renormalization group (RNG) k-ε turbulence model and the single-step chemical reaction mechanism. This numerical approach was validated by comparing predicted results with published experimental shadowgraphs and velocity and temperature measurements. When the pressure of the wall-injector increases, the performance of the combustor decreases. At the same inflow condition, this may lead to a scram-to-ram mode transition. The cavity adopted in this study would prevent pre-combustion shock waves from pushing out of the isolator and help to stabilize the flow field, but it would decrease the mixing and combustion efficiencies.
中文概要
目的
超燃冲压发动机燃烧室中氢气的燃烧性能引起了研究者的广泛兴趣。本文旨在探讨不同压比下超燃冲压发动机燃烧室的燃烧性能以及壁面凹腔的影响,为双模态超燃冲压发动机燃烧室设计提供参考。
创新点
1. 研究压比变化过程中超燃向亚燃的转换过程;2. 研究壁面凹腔设置对模态转换过程的影响。
方法
采用数值模拟方法研究不同来流条件下,压比和壁面凹腔设置对基于支板的超燃冲压发动机燃烧室中模态转换过程的影响。
结论
1. 壁面喷注压强对流场结构影响很大,特别是对于亚燃到超燃的模态转换过程和燃烧性能,当壁面喷注压强大约为支板喷注压强一半时,效果最好;2. 壁面凹腔能帮助稳定流场,但也会带来一定的混合效率和燃烧效率损失,同时壁面凹腔能帮助延迟从超燃模态向亚燃模态的转换时间,这也从一定程度上说明带凹腔的燃烧室更加适合于超燃模态。
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References
Cao RF, Chang JT, Tang JF, et al., 2014. Study on combustion mode transition of hydrogen fueled dual-mode scramjet engine based on thermodynamic cycle analysis. International Journal of Hydrogen Energy, 39(36):21251–21258. https://doi.org/10.1016/j.ijhydene.2014.10.082
Choubey G, Pandey KM, 2016. Investigation on the effects of operating variables on the performance of two-strut scramjet combustor. International Journal of Hydrogen Energy, 41(45):20753–20770. https://doi.org/10.1016/j.ijhydene.2016.09.157
Choudhuri AR, Gollahalli SR, 2000. Combustion characteristics of hydrogen-hydrocarbon hybrid fuels. International Journal of Hydrogen Energy, 25(5):451–462. https://doi.org/10.1016/S0360-3199(99)00027-0
Curran ET, 2001. Scramjet engines: the first forty years. Journal of Propulsion and Power, 17(6):1138–1148. https://doi.org/10.2514/2.5875
Fluent, 2006. Fluent 6.3 User’s Guide. Fluent, Inc., Lebanon, USA.
Fureby C, Nordin-Bates K, Petterson K, et al., 2015. A computational study of supersonic combustion in strut injector and hypermixer flow fields. Proceedings of the Combustion Institute, 35(2):2127–2135. https://doi.org/10.1016/j.proci.2014.06.113
Gang Q, Zhou LY, Qin Z, et al., 2011. Experimental investigation of strut-cavity flameholder technology in liquid hydrocarbon fueled scramjet combustor. Journal of Propulsion Technology, 32:680–683 (in Chinese).
Gruber MR, 2004. Mixing and combustion studies using cavity-based flameholders in a supersonic flow. Journal of Propulsion and Power, 20(5):769–778. https://doi.org/10.2514/1.5360
Guerra R, Waidmann W, Laible C, 1991. An experimental investigation of the combustion of a hydrogen jet injected parallel in a supersonic air stream. AIAA 3rd International Aerospace Planes Conference, AIAA Paper 91-5102.
Huang W, 2015. Investigation on the effect of strut configurations and locations on the combustion performance of a typical scramjet combustor. Journal of Mechanical Science and Technology, 29(12):5485–5496. https://doi.org/10.1007/s12206-015-1150-6
Huang W, 2016. Transverse jet in supersonic crossflows. Aerospace Science and Technology, 50:183–195. https://doi.org/10.1016/j.ast.2016.01.001
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. https://doi.org/10.1631/jzus.A1300096
Huang W, Yan L, 2016. Numerical investigation on the ramscram transition mechanism in a strut-based dual-mode scramjet combustor. International Journal of Hydrogen Energy, 41(8):4799–4807. https://doi.org/10.1016/j.ijhydene.2016.01.062
Huang W, Wang ZG, Jin L, et al., 2011a. Effect of cavity location on combustion flow field of integrated hypersonic vehicle in near space. Journal of Visualization, 14(4):339–351. https://doi.org/10.1007/s12650-011-0100-3
Huang W, Wang ZG, Pourkashanian M, et al., 2011b. Numerical investigation on the shock wave transition in a three-dimensional scramjet isolator. Acta Astronautica, 68(11–12): 1669–1675. https://doi.org/10.1016/j.actaastro.2010.12.011
Huang W, Wang ZG, Luo SB, et al., 2011c. Parametric effects on the combustion flow field of a typical strut-based scramjet combustor. Chinese Science Bulletin, 56(35): 3871–3877. https://doi.org/10.1007/s11434-011-4823-2
Huang W, Pourkashanian M, Ma L, et al., 2012a. Effect of geometric parameters on the drag of the cavity fameholder based on the variance analysis method. Aerospace Science and Technology, 21(1):24–30. https://doi.org/10.1016/j.ast.2011.04.009
Huang W, Ma L, Pourkashanian M, et al., 2012b. Flow-field analysis of a typical hydrogen-fueled dual-mode scramjet combustor. Journal of Aerospace Engineering, 25(3): 336–346. https://doi.org/10.1061/(ASCE)AS.1943-5525.0000136
Huang W, Liu WD, Li SB, et al., 2012c. Influences of the turbulence model and the slot width on the transverse slot injection flow field in supersonic flows. Acta Astronautica, 73:1–9. https://doi.org/10.1016/j.actaastro.2011.12.003
Huang W, Wang ZG, Yan L, et al., 2012d. Numerical validation and parametric investigation on the cold flow field of a typical cavity-based scramjet combustor. Acta Astronautica, 80:132–140. https://doi.org/10.1016/j.actaastro.2012.06.004
Huang W, Li SB, Yan L, et al., 2013. Performance evaluation and parametric analysis on cantilevered ramp injector in supersonic flows. Acta Astronautica, 84:141–152. https://doi.org/10.1016/j.actaastro.2012.11.011
Huang W, Jin L, Yan L, et al., 2014a. Influence of jet-tocrossflow pressure ratio on nonreacting and reacting processes in a scramjet combustor with backward-facing steps. International Journal of Hydrogen Energy, 39: 21242–21250. https://doi.org/10.1016/j.ijhydene.2014.10.073
Huang W, Yan L, Tan JG, 2014b. Survey on the mode transition technique in combined cycle propulsion systems. Aerospace Science and Technology, 39:685–691. https://doi.org/10.1016/j.ast.2014.07.006
Huang W, Li SB, Yan L, et al., 2015. Multiobjective design optimization of a cantilevered ramp injector using the surrogate-assisted evolutionary algorithm. Journal of Aerospace Engineering, 28:04014138. https://doi.org/10.1061/(ASCE)AS.1943-5525.0000477
Huang W, Li MH, Yan L, 2016a. Mixing augmentation mechanism induced by the pseudo shock wave in transverse gaseous injection flow fields. International Journal of Hydrogen Energy, 41:10961–10968. https://doi.org/10.1016/j.ijhydene.2016.04.078
Huang W, Li LQ, Yan L, et al., 2016b. Numerical exploration of mixing and combustion in a dual-mode combustor with backward-facing steps. Acta Astronautica, 127:572–578. https://doi.org/10.1016/j.actaastro.2016.06.043
Huang W, Li MH, Ding F, 2016c. Supersonic mixing augmentation mechanism induced by a wall-mounted cavity configuration. Journal of Zhejiang University-SCIENCE A (Applied Physics & Engineering), 17(1):45–53. https://doi.org/10.1631/jzus.A1500244
Kim CH, Jeung IS, Choi B, et al., 2011. Effect of fuel injection location on a plasma jet assisted combustion with a backward-facing step. Proceedings of the Combustion Institute, 33:2375–2382. https://doi.org/10.1016/j.proci.2010.07.057
Kummitha OR, Pandey KM, Gupta R, 2018. CFD analysis of a scramjet combustor with cavity based flame holders. Acta Astronautica, 144:244–253. https://doi.org/10.1016/j.actaastro.2018.01.005
Mahto NK, Choubey G, Suneetha L, et al., 2016. Effect of variation of length-to-depth ratio and Mach number on the performance of a typical double cavity scramjet combustor. Acta Astronautica, 128:540–550. https://doi.org/10.1016/j.actaastro.2016.08.010
Micka DJ, Driscoll JF, 2009. Combustion characteristics of a dual-mode scramjet combustor with cavity flameholder. Proceedings of the Combustion Institute, 32(2):2397–2404. https://doi.org/10.1016/j.proci.2008.06.192
Oevermann M, 2000. Numerical investigation of turbulent hydrogen combustion in a SCRAMJET using flamelet modeling. Aerospace Science Technology, 4(7):463–480. https://doi.org/10.1016/S1270-9638(00)01070-1
Ogawa H, 2016. Effects of injection angle and pressure on mixing performance of fuel injection via various geometries for upstream-fuel-injected scramjets. Acta Astronautica, 128:485–498. https://doi.org/10.1016/j.actaastro.2016.08.008
Qin J, Bao W, Zhou WX, et al., 2010. Flow and heat transfer characteristics in fuel cooling channels of a recooling cycle. International Journal of Hydrogen Energy, 35(19): 10589–10598. https://doi.org/10.1016/j.ijhydene.2010.08.019
Segal C, 2009. The Scramjet Engine Processes and Characteristics. Cambridge University Press, UK.
Smirnov NN, Nikitin VF, 2014. Modeling and simulation of hydrogen combustion in engines. International Journal of Hydrogen Energy, 39(2):1122–1136. https://doi.org/10.1016/j.ijhydene.2013.10.097
Smirnov NN, Nikitin VF, Phylippov YG, 2010. Deflagration to detonation transition in gases in tubes with cavities. Journal of Engineering Physics and Thermophysics, 83(6):1287–1316. https://doi.org/10.1007/s10891-010-0448-6
Smirnov NN, Betelin VB, Nikitin VF, et al., 2015. Accumulation of errors in numerical simulations of chemically reacting gas dynamics. Acta Astronautica, 117:338–355. https://doi.org/10.1016/j.actaastro.2015.08.013
Tian Y, Xiao BG, Zhang SP, et al., 2015. Experimental and computational study on combustion performance of a kerosene fueled dual-mode scramjet engine. Aerospace Science and Technology, 46:451–458. https://doi.org/10.1016/j.ast.2015.09.002
Turner JC, Smart MK, 2010. Application of inlet injection to a three-dimensional scramjet at Mach 8. AIAA Journal, 48(4):829–838. https://doi.org/10.2514/1.J050052
Yan L, Liao L, Huang W, et al., 2018. Nonlinear process in the mode transition in typical strut-based and cavity-strut based scramjet combustors. Acta Astronautica, 145:250–262. https://doi.org/10.1016/j.actaastro.2018.01.061
Zhang Y, Zhu SH, Chen B, et al., 2016. Hysteresis of mode transition in a dual-struts based scramjet. Acta Astronautica, 128:147–159. https://doi.org/10.1016/j.actaastro.2016.07.025
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Liao, L., Yan, L., Huang, W. et al. Mode transition process in a typical strut-based scramjet combustor based on a parametric study. J. Zhejiang Univ. Sci. A 19, 431–451 (2018). https://doi.org/10.1631/jzus.A1700617
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DOI: https://doi.org/10.1631/jzus.A1700617