Investigation of the combustion process in an ethylene-fueled scramjet combustor

ZHONG Fuyu; LE Jialing; TIAN Ye; YUE Maoxiong

doi:10.11729/syltlx20200093

Volume 35 Issue 1

Feb. 2021

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Article Navigation > Journal of Experiments in Fluid Mechanics > 2021 > 35(1): 34-43

ZHONG Fuyu, LE Jialing, TIAN Ye, et al. Investigation of the combustion process in an ethylene-fueled scramjet combustor[J]. Journal of Experiments in Fluid Mechanics, 2021, 35(1): 34-43. doi: 10.11729/syltlx20200093

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Investigation of the combustion process in an ethylene-fueled scramjet combustor

doi: 10.11729/syltlx20200093

Science and Technology on Scramjet Laboratory, China Aerodynamics Research and Development Center, Mianyang Sichuan 621000, China

Received Date: 2020-08-02
Rev Recd Date: 2020-09-26
Publish Date: 2021-02-25

Abstract

Abstract

An experimental investigation was conducted in a direct-connect supersonic combustion facility simulating the inflow condition of Ma=2.0 to investigate the combustion process in an ethylene-fueled scramjet combustor with cavity and pilot hydrogen. The structure of the flow field and the flame development were visualized using the schlieren imaging, the flame luminosity imaging, the CH luminosity imaging and the planar laser-induced fluorescence (PLIF) of the OH radical. The equivalence ratios of pilot hydrogen and ethylene were about 0.33 and 0.10, respectively. The whole combustion process could be divided into six stages. In the first stage, there was a non-reaction cold flow before the hydrogen injection. And the frequency of oscillation was measured to be around 400 Hz, experimentally. In the second stage, the flow characteristics before the pilot hydrogen ignition were revealed, due to the hydrogen injection an oblique shock wave was generated, reflected on the bottom wall, and then interacted with the shock waves below the cavity, thus leading to the increase of the monitor pressure. The third stage was the hydrogen combustion, including ignition and flame stabilization. The process from the ignition of pilot hydrogen to the combustion stabilization lasted around 26.0 ms. In the first 0.1 ms, the ignition of pilot hydrogen had great effect on the flow field structures. The moving speed of the shock train caused by the combustion of pilot hydrogen was around 20 m/s. The stabilization mode of the pilot hydrogen flame was cavity recirculation stabilized combustion. The fourth stage was the intense combustion process of hydrogen and ethylene. The shock waves were pushed into the isolator, and thus exceeded the observation range. The ethylene flame stabilization mode was shear layer stabilized combustion. The combustion characteristics of ethylene were revealed in the fifth stage. When the pilot hydrogen was ceased, the ethylene flame moved from the cavity step to the cavity ramp. The last stage involved the combustion and flame blowout of pure ethylene. Preliminary analysis indicates that the CH luminosity images of ethylene combustion can be used to investigate combustion efficiency qualitatively.
- scramjet combustor,
- ethylene,
- ignition,
- flame stabilization,
- combustion charac-teristics

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References(20)

References

[1]	URZAY J. Supersonic combustion in air-breathing propulsion systems for hypersonic flight[J]. Annual Review of Fluid Mechanics, 2018, 50(1): 593-627. doi: 10.1146/annurev-fluid-122316-045217
[2]	田野, 乐嘉陵, 杨顺华, 等. 氢燃料超燃燃烧室流场结构和火焰传播规律试验研究[J]. 实验流体力学, 2019, 33(1): 72-78. doi: 10.11729/syltlx20180027 TIAN Y, LE J L, YANG S H, et al. Experimental study on flow structure and flame development in a hydrogen-fueled supersonic combustor[J]. Journal of Experiments in Fluid Mechanics, 2019, 33(1): 72-78. doi: 10.11729/syltlx20180027
[3]	吴戈, 李韵, 万明罡, 等. 平面激光诱导荧光技术在超声速燃烧火焰结构可视化中的应用[J]. 实验流体力学, 2020, 34(3): 70-77. doi: 10.11729/syltlx20190168 WU G, LI Y, WAN M G, et al. Visualization of flame structure in supersonic combustion by Planar Laser Induced Fluorescence technique[J]. Journal of Experiments in Fluid Mechanics, 2020, 34(3): 70-77. doi: 10.11729/syltlx20190168
[4]	RUAN J L, DOMINGO P, RIBERT G. Analysis of combustion modes in a cavity based scramjet[J]. Combustion and Flame, 2020, 215: 238-251. doi: 10.1016/j.combustflame.2020.01.034
[5]	GORDON R L, STÅRNER S H, MASRI A R, et al. Further characterisation of lifted hydrogen and methane flames issuing into a vitiated coflow[C]//Proc of the 5th Asia-Pacific Conference on Combustion. 2005.
[6]	GORDON R L, MASRI A R, MASTORAKOS E. Simu-ltaneous Rayleigh temperature, OH- and CH₂O-LIF imaging of methane jets in a vitiated coflow[J]. Combustion and Flame, 2008, 155(1-2): 181-195. doi: 10.1016/j.combustflame.2008.07.001
[7]	MASTORAKOS E. Ignition of turbulent non-premixed flames[J]. Progress in Energy and Combustion Science, 2009, 35(1): 57-97. doi: 10.1016/j.pecs.2008.07.002
[8]	张弯洲, 乐嘉陵, 杨顺华, 等. Ma4下超燃发动机乙烯点火及火焰传播过程试验研究[J]. 实验流体力学, 2016, 30(3): 40-46, 84. doi: 10.11729/syltlx20150161 ZHANG W Z, LE J L, YANG S H, et al. Experimental research on ethylene ignition and flame propagation processes for scramjet at Ma4[J]. Journal of Experiments in Fluid Mechanics, 2016, 30(3): 40-46, 84. doi: 10.11729/syltlx20150161
[9]	BRIESCHENK S, O'BYRNE S, KLEINE H. Laser-induced plasma ignition studies in a model scramjet engine[J]. Combustion and Flame, 2013, 160(1): 145-148. doi: 10.1016/j.combustflame.2012.08.011
[10]	BRIESCHENK S, O'BYRNE S, KLEINE H. Ignition charac-teristics of laser-ionized fuel injected into a hypersonic crossflow[J]. Combustion and Flame, 2014, 161(4): 1015-1025. doi: 10.1016/j.combustflame.2013.09.024
[11]	KUMARAN K, BABU V. Investigation of the effect of chemistry models on the numerical predictions of the supersonic combustion of hydrogen[J]. Combustion and Flame, 2009, 156(4): 826-841. doi: 10.1016/j.combustflame.2009.01.008
[12]	NAKAYA S, TSUE M, KONO M, et al. Effects of thermally cracked component of n-dodecane on supersonic combustion behaviors in a scramjet model combustor[J]. Combustion and Flame, 2015, 162(10): 3847-3853. doi: 10.1016/j.combustflame.2015.07.021
[13]	何粲, 邢建文, 肖保国, 等. 矩形截面超燃发动机不同燃烧模态下的流场特征[J]. 实验流体力学, 2018, 32(4): 12-19. doi: 10.11729/syltlx20180022 HE C, XING J W, XIAO B G, et al. Investigation on flow field characteristics of a rectangular scramjet in different combustion modes[J]. Journal of Experiments in Fluid Mechanics, 2018, 32(4): 12-19. doi: 10.11729/syltlx20180022
[14]	QIN Q Y, AGARWAL R, ZHANG X B. A novel method for flame stabilization in a strut-based scramjet combustor[J]. Combustion and Flame, 2019, 210: 292-301. doi: 10.1016/j.combustflame.2019.08.038
[15]	FÖRSTER F J, DRÖSKE N C, BVHLER M N, et al. Analysis of flame characteristics in a scramjet combustor with staged fuel injection using common path focusing schlieren and flame visualization[J]. Combustion and Flame, 2016, 168: 204-215. doi: 10.1016/j.combustflame.2016.03.010
[16]	AN B, YANG L C, WANG Z G, et al. Characteristics of laser ignition and spark discharge ignition in a cavity-based supersonic combustor[J]. Combustion and Flame, 2020, 212: 177-188. doi: 10.1016/j.combustflame.2019.10.030
[17]	TIAN Y, YANG S H, LE J L, et al. Investigation of combustion process of a kerosene fueled combustor with air throttling[J]. Combustion and Flame, 2017, 179: 74-85. doi: 10.1016/j.combustflame.2017.01.021
[18]	TIAN Y, XIAO B G, ZHANG S P, et al. Experimental and computational study on combustion performance of a kerosene fueled dual-mode scramjet engine[J]. Aerospace Science and Technology, 2015, 46: 451-458. doi: 10.1016/j.ast.2015.09.002
[19]	TIAN Y, YANG S H, LE J L. Numerical study on effect of air throttling on combustion mode formation and transition in a dual-mode scramjet combustor[J]. Aerospace Science and Technology, 2016, 52: 173-180. doi: 10.1016/j.ast.2016.02.027
[20]	钟富宇, 乐嘉陵, 韩亦宇, 等. 当量比对氢燃料超燃燃烧室流场结构和燃烧模态影响研究[J]. 推进技术, 2019, 40(2): 324-330. doi: 10.13675/j.cnki.tjjs.170776 ZHONG F Y, LE J L, HAN Y Y, et al. Investigation for effects of equivalence ratio on flow structure and combustion mode in a hydrogen fueled scramjet combustor[J]. Journal of Propulsion Technology, 2019, 40(2): 324-330. doi: 10.13675/j.cnki.tjjs.170776