Abstract
To investigate the characteristics of vaporized RP-3 kerosene combustion in a scramjet combustor enhanced by the micro vortex generator (MVG), a series of experiments are carried out based on the advanced combustion diagnosis technique. The high-enthalpy incoming flow is accelerated to supersonic through a Mach 2.52 nozzle, the total pressure and temperature of which are 1.6 MPa and 1486 K, respectively. The effect of MVG on the ignition process, flame distribution, and combustor pressure along the bottom wall is well revealed, and the effects of the position and number of MVGs on stable combustion performance are analyzed. The results indicate that the development processes of the initial flame kernel with and without an MVG during ignition process show a similar behavior. The installation of an MVG can lift the shear layer, promote the penetration of flame deeper into the mainstream, and expand the area of the reactive region. Reducing the distance between the MVG and the injection position and increasing the number of MVGs are regarded as effective ways of improving the mixing degree of fuel and air with a resultant intensification of chemical reactions and flame luminescence. The effect of mixing and subsequent combustion is enhanced by shortening the distance between the MVG and the injection position. As the layout schemes of the MVG vary, the pressure distribution between the injection position and the leading edge of the cavity changes considerably, while that in the cavity remains almost constant. Increasing the number of MVGs is also beneficial for improving the premixed degree of fuel and incoming flow and results in more violent chemical reactions downstream of the cavity.
摘要
目的
研究微型涡流发生器(MVG)对超燃冲压发动机燃烧室中气化RP-3煤油燃烧的增强作用。
创新点
1. 实验研究了微型涡流发生器对超声速气流中气化煤油燃烧的增强作用;2. 分析了微型涡流发生器布置位置和数量的影响。
方法
1. 在超燃冲压发动机直连式测试平台上进行气化RP-3煤油燃烧的实验研究;2. 比较喷注位置下游有无微型涡流发生器时点火过程和凹腔稳焰的区别,验证微型涡流发生器对燃烧的促进作用;3. 探讨微型涡流发生器位置和数量的影响。
结论
1. 有无涡流发生器对点火过程影响较小,但微型涡流发生器能够在火焰稳定后促进燃烧; 微型涡流发生器可以提升剪切层,使火焰区域更深入主流。2. 缩短微型涡流发生器与喷注位置之间的距离有利于促进燃料与空气的预混程度,能够促进燃料的混合和随后的燃烧效果; 本文中缩短两者之间的距离能够将光强提升15.6%;微型涡流发生器的位置主要影响喷注位置和凹腔之间的室压,而对凹腔附近室压影响很小。3. 增加微型涡流发生器的数量对燃烧前燃料与空气的预混效果有促进作用,使下游的化学反应更加剧烈; 然而,微型涡流发生器的位置对燃烧性能的影响可能更大。
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References
Aguilera C, Yu KH, 2015. Supersonic mixing enhancement using fin-guided fuel injection. Journal of Propulsion and Power, 31(6):1532–1543. https://doi.org/10.2514/1.B35685
Aguilera C, Yu KH, 2017. Effect of fin-guided fuel injection on dual-mode scramjet operation. Journal of Propulsion and Power, 33(4):927–938. https://doi.org/10.2514/1.B36305
Baigmohammadi M, Tabejamaat S, Javanbakht Z, 2019. Numerical study of methane-oxygen premixed flame characteristics in non-adiabatic cylindrical meso-scale reactors with the backward-facing step. Iranian Journal of Science and Technology, Transactions of Mechanical Engineering, 43(S1):117–140. https://doi.org/10.1007/s40997-018-0144-2
Bao H, Zhou J, Pan Y, 2015. Effect of cavity configuration on kerosene spark ignition in a scramjet combustor at Ma 4.5 flight condition. Acta Astronautica, 117:368–375. https://doi.org/10.1016/j.actaastro.2015.08.012
Ben-Yakar A, Hanson RK, 2001. Cavity flame-holders for ignition and flame stabilization in scramjets: an overview. Journal of Propulsion and Power, 17(4):869–877. https://doi.org/10.2514/2.5818
Choubey G, Devarajan Y, Huang W, et al., 2019. Recent advances in cavity-based scramjet engine-a brief review. International Journal of Hydrogen Energy, 44(26):13895–13909. https://doi.org/10.1016/j.ijhydene.2019.04.003
Fan XJ, Yu G, Li JG, et al., 2006. Investigation of vaporized kerosene injection and combustion in a supersonic model combustor. Journal of Propulsion and Power, 22(1):103–110. https://doi.org/10.2514/1.15427
Ferraiuolo M, Petrillo W, Riccio A, 2017. On the thermostructural response of a composite closeout in a regeneratively cooled thrust chamber. Aerospace Science and Technology, 71:402–411. https://doi.org/10.1016/j.ast.2017.09.041
Huang W, Du ZB, Yan L, et al., 2019. Supersonic mixing in airbreathing propulsion systems for hypersonic flights. Progress in Aerospace Sciences, 109:100545. https://doi.org/10.1016/j.paerosci.2019.05.005
Huang W, Chang JT, Yan L, 2020. Mixing and combustion in supersonic/hypersonic flows. Journal of Zhejiang University-SCIENCE A (Applied Physics & Engineering), 21(7):609–613. https://doi.org/10.1631/jzus.A20MCSF1
Jeong E, O’Byrne S, Jeung IS, et al., 2020. The effect of fuel injection location on supersonic hydrogen combustion in a cavity-based model scramjet combustor. Energies, 13(1):193. https://doi.org/10.3390/en13010193
Kummitha OR, Pandey KM, Gupta R, 2018a. 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
Kummitha OR, Pandey KM, Gupta R, 2018b. Optimization of scramjet performance with different fuel injection techniques and flame holder cavities. Acta Astronautica, 152:908–919. https://doi.org/10.1016/j.actaastro.2018.09.026
Le JL, Yang SH, Li HB, 2012. Analysis and correlation of flame stability limits in supersonic flow with cavity flameholder. Proceedings of the 18th AIAA/3AF International Space Planes and Hypersonic Systems and Technologies Conference, p.2012–5948. https://doi.org/10.2514/6.2012-5948
Li CL, Zhao X, Xia ZX, et al., 2019. Influence of the vortex generator on the performance of solid rocket scramjet combustor. Acta Astronautica, 164:174–183. https://doi.org/10.1016/j.actaastro.2019.08.002
Li LQ, Huang W, Yan L, 2017a. Mixing augmentation induced by a vortex generator located upstream of the transverse gaseous jet in supersonic flows. Aerospace Science and Technology, 68:77–89. https://doi.org/10.1016/j.ast.2017.05.016
Li LQ, Huang W, Yan L, et al., 2017b. Mixing enhancement and penetration improvement induced by pulsed gaseous jet and a vortex generator in supersonic flows. International Journal of Hydrogen Energy, 42(30):19318–19330. https://doi.org/10.1016/j.ijhydene.2017.06.014
Li ZX, Barzegar Gerdroodbary M, Moradi R, et al., 2020a. Effect of inclined block on fuel mixing of multi hydrogen jets in scramjet engine. Aerospace Science and Technology, 105:106035. https://doi.org/10.1016/j.ast.2020.106035
Li ZX, Barzegar Gerdroodbary M, Sheikholeslami M, et al., 2020b. Mixing enhancement of multi hydrogen jets through the cavity flameholder with extended pylon. Acta Astronautica, 175:300–307. https://doi.org/10.1016/j.actaastro.2020.06.002
Liu CY, Zhao YH, Wang ZG, et al., 2017. Dynamics and mixing mechanism of transverse jet injection into a supersonic combustor with cavity flameholder. Acta Astronautica, 136:90–100. https://doi.org/10.1016/j.actaastro.2017.03.010
Liu CY, Sun MB, Wang HB, et al., 2020. Ignition and flame stabilization characteristics in an ethylene-fueled scramjet combustor. Aerospace Science and Technology, 106:106186. https://doi.org/10.1016/j.ast.2020.106186
Liu XL, Barzegar Gerdroodbary M, Sheikholeslami M, et al., 2020. Effect of strut angle on performance of hydrogen multi-jets inside the cavity at combustion chamber. International Journal of Hydrogen Energy, 45(55):31179–31187. https://doi.org/10.1016/j.ijhydene.2020.08.124
Neill SM, Pesyridis A, 2017. Modeling of supersonic combustion systems for sustained hypersonic flight. Energies, 10(11):1900. https://doi.org/10.3390/en10111900
Ning W, Yu P, Jin Z, 2013. Research status of active cooling of endothermic hydrocarbon fueled scramjet engine. Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering, 227(11):1780–1794. https://doi.org/10.1177/0954410012463642
Pillai AL, Nagao J, Awane R, et al., 2020. Influences of liquid fuel atomization and flow rate fluctuations on spray combustion instabilities in a backward-facing step combustor. Combustion and Flame, 220:337–356. https://doi.org/10.1016/j.combustflame.2020.06.031
Qiu HC, Zhang JL, Sun XX, et al., 2020. Flowing residence characteristics in a dual-mode scramjet combustor equipped with strut flame holder. Aerospace Science and Technology, 99:105718. https://doi.org/10.1016/j.ast.2020.105718
Ravindran M, Bricalli M, Pudsey A, et al., 2019. Mixing characteristics of cracked gaseous hydrocarbon fuels in a scramjet combustor. Acta Astronautica, 162:168–184. https://doi.org/10.1016/j.actaastro.2019.06.010
Saravanan G, Suresh C, 2012. Numerical simulation of mixing enhancement in scramjet using micro vortex generator. Procedia Engineering, 38:3969–3976. https://doi.org/10.1016/j.proeng.2012.06.454
Shi DY, Song WY, Wang YH, et al., 2017. Effects of cavity configurations on flameholding and performances of kerosene fueled scramjet combustor. International Journal of Turbo & Jet-Engines, 34(3):211–220. https://doi.org/10.1515/tjj-2015-0058
Tuncer O, 2010. Combustion in a ramjet combustor with cavity flame holder. Proceedings of the 48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition, p.18086–18097. https://doi.org/10.2514/6.2010-1532
Urzay J, 2018. Supersonic combustion in air-breathing propulsion systems for hypersonic flight. Annual Review of Fluid Mechanics, 50:593–627. https://doi.org/10.1146/annurev-fluid-122316-045217
Vincent-Randonnier A, Rouxel B, Roux P, et al., 2008. Experimental investigations on the self-ignition of a thermally decomposed endothermic fuel in hot supersonic air flow in the MPP-LAERTE combustion test bench. Proceedings of the 15th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, p.1501–1508. https://doi.org/10.2514/6.2008-2676
Yang K, Pan Y, Wang ZG, et al., 2020. Experimental investigation of the ignition characteristics of vaporized RP-3 kerosene in supersonic flow. Acta Astronautica, 174:1–10. https://doi.org/10.1016/j.actaastro.2020.04.022
Zhang DQ, Song WY, 2017. Experimental study of cone-struts and cavity flameholders in a kerosene-fueled round scramjet combustor. Acta Astronautica, 139:24–33. https://doi.org/10.1016/j.actaastro.2017.06.025
Zhang JC, Wang ZG, Sun MB, et al., 2020. Effect of the backward facing step on a transverse jet in supersonic cross-flow. Energies, 13(16):4170. https://doi.org/10.3390/en13164170
Zhang JL, Chang JT, Tian HM, et al., 2020. Flame interaction characteristics in scramjet combustor equipped with strut/wall combined fuel injectors. Combustion Science and Technology, 192(10):1863–1886. https://doi.org/10.1080/00102202.2019.1627342
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This work is supported by the National Natural Science Foundation of China (No. 12002373).
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Dong-peng JIA designed the research. Dong-peng JIA, Yu PAN, and Ning WANG processed the corresponding data. Dong-peng JIA wrote the first draft of the manuscript. Kai YANG helped to organize the manuscript. Xi-peng LI revised and edited the final version.
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Dong-peng JIA, Kai YANG, Yu PAN, Xi-peng LI, and Ning WANG declare that they have no conflict of interest.
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Jia, Dp., Yang, K., Pan, Y. et al. Effect of the micro vortex generator on the characteristics of vaporized RP-3 kerosene combustion in supersonic flows. J. Zhejiang Univ. Sci. A 23, 405–414 (2022). https://doi.org/10.1631/jzus.A2000620
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DOI: https://doi.org/10.1631/jzus.A2000620