Experimental study on the effect of equivalent ratio on working characteristics of gasoline fuel two-phase rotating detonation engine

GE Gaoyang; MA Yuan; HOU Shizhuo; XIA Zhenjuan; MA Hu; DENG Li; ZHOU Changsheng

doi:10.11883/bzycj-2020-0465

Volume 41 Issue 11

Nov. 2021

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GE Gaoyang, MA Yuan, HOU Shizhuo, XIA Zhenjuan, MA Hu, DENG Li, ZHOU Changsheng. Experimental study on the effect of equivalent ratio on working characteristics of gasoline fuel two-phase rotating detonation engine[J]. Explosion And Shock Waves, 2021, 41(11): 112102. doi: 10.11883/bzycj-2020-0465

Citation:

GE Gaoyang, MA Yuan, HOU Shizhuo, XIA Zhenjuan, MA Hu, DENG Li, ZHOU Changsheng. Experimental study on the effect of equivalent ratio on working characteristics of gasoline fuel two-phase rotating detonation engine[J]. Explosion And Shock Waves, 2021, 41(11): 112102. doi: 10.11883/bzycj-2020-0465

Citation:

GE Gaoyang, MA Yuan, HOU Shizhuo, XIA Zhenjuan, MA Hu, DENG Li, ZHOU Changsheng. Experimental study on the effect of equivalent ratio on working characteristics of gasoline fuel two-phase rotating detonation engine[J]. Explosion And Shock Waves, 2021, 41(11): 112102. doi: 10.11883/bzycj-2020-0465

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Experimental study on the effect of equivalent ratio on working characteristics of gasoline fuel two-phase rotating detonation engine

doi: 10.11883/bzycj-2020-0465

1.
School of Mechanical Engineering, Nanjing University of Science and Technology, Nanjing 210094, Jiangsu, China
2.
Department of Aeronautical Mechanical Engineering and Command, Qingdao Campus of Naval Aeronautical University, Qingdao 266100, Shandong, China
3.
Institute of Chemical Materials, China Academy of Engineering Physics, Mianyang 621999, Sichuan, China

Received Date: 2020-12-15
Rev Recd Date: 2021-03-25

Available Online: 2021-09-30

Publish Date: 2021-11-23

Abstract

Abstract

To understand the effect of equivalent ratio on the working characteristics of gasoline fuel two-phase rotating detonation engine, a gas-liquid two-phase rotating detonation experimental study with high total temperature air as oxidant has been carried out in this work. The outer diameter, inner diameter and length of rotating detonation engine annular combustor are 202, 166 and 155 mm, respectively. Gasoline and high temperature air are injected into the combustor through a nozzle-gap impinging model constructed of high pressure atomizing nozzles and annular gap to improve the mixing effect and chemical reactivity of propellant. A pre-detonator tube is used as ignition device. In experiments, the equivalent ratio of propellant is controlled by changing the gasoline mass flow rate with constant air mass flow rate. Based on high frequency dynamic pressure signals and average static pressure measured in the combustor, the propagation mode and propagation characteristics of the gas-liquid two-phase rotating detonation wave and working characteristics of the engine were analyzed in details. Experimental results show that continuous self-sustained propagation of rotating detonation wave is realized in the combustor during the equivalent ratio ranging from 0.79 to 1.25. With the increase of the equivalent ratio, the propagation mode of detonation wave transforms from double wave collision/single wave mixed mode to single wave mode. By reducing the equivalent ratio to 0.61−0.66, the propagation stability of detonation wave becomes worse, and the propagation mode transforms to the intermittent detonation or sporadic detonation. When reducing the equivalent ratio to 0.53, the detonation initiation fails. In addition, with the increase of the equivalent ratio, both the average absolute pressure in the combustor and the average propagation frequency of detonation wave increase and then decrease, and the maximum value appears around the equivalent ratio of 1.19. Under this condition, the best experimental results are obtained. The average propagation frequency of detonation wave is 1 900.9 Hz, and corresponding average propagation velocity is 1 110.8 m/s, which are consistent with the main frequency obtained from Fast Fourier Transform of high frequency pressure signal. There is a heavy velocity deficit existing during the propagation of detonation wave.
- equivalent ratio,
- gas-liquid two-phase,
- rotating detonation,
- high total temperature air,
- propagation mode,
- propagation frequency

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References(19)

References

[1]	BYKOVSKII F A, MITROFANOV V V, VEDERNIKOV E F. Continuous detonation combustion of fuel-air mixtures [J]. Combustion, Explosion and Shock Waves, 1997, 33(3): 344–353. DOI: 10.1007/BF02671875.
[2]	BYKOVSKII F A, ZHDAN S A, VEDERNIKOV E F. Continuous spin detonation of fuel-air mixtures [J]. Combustion, Explosion and Shock Waves, 2006, 42(4): 463–471. DOI: 10.1007/s10573-006-0076-9.
[3]	BYKOVSKII F A, ZHDAN S A, VEDERNIKOV E F. Continuous spin detonations [J]. Journal of Propulsion and Power, 2006, 22(6): 1204–1216. DOI: 10.2514/1.17656.
[4]	BYKOVSKII F A, ZHDAN S A, VEDERNIKOV E F. Initiation of detonation of fuel-air mixtures in a flow-type annular combustor [J]. Combustion, Explosion, and Shock Waves, 2014, 50(2): 214–222. DOI: 10.1134/S0010508214020130.
[5]	BYKOVSKII F A, ZHDAN S A, VEDERNIKOV E F. Continuous spin detonation of a heterogeneous kerosene-air mixture with addition of hydrogen [J]. Combustion, Explosion, and Shock Waves, 2016, 52(3): 371–373. DOI: 10.1134/S0010508216030187.
[6]	BYKOVSKII F A, ZHDAN S A, VEDERNIKOV E F. Continuous detonation of the liquid kerosene-air mixture with addition of hydrogen or syngas [J]. Combustion, Explosion, and Shock Waves, 2019, 55(5): 589–598. DOI: 10.1134/S0010508219050101.
[7]	FROLOV S M, AKSENOV V S, IVANOV V S, et al. Continuous detonation combustion of ternary “hydrogen-liquid propane-air” mixture in annular combustor [J]. International Journal of Hydrogen Energy, 2017, 42(26): 16808–16820. DOI: 10.1016/j.ijhydene.2017.05.138.
[8]	KINDRACKI J. Experimental studies of kerosene injection into a model of a detonation chamber [J]. Journal of Power Technologies, 2012, 92(2): 80–89.
[9]	KINDRACKI J. Study of detonation initiation in kerosene-oxidizer mixtures in short tubes [J]. Shock Waves, 2014, 24(6): 603–618. DOI: 10.1007/s00193-014-0519-2.
[10]	KINDRACKI J. Experimental research on rotating detonation in liquid fuel-gaseous air mixtures [J]. Aerospace Science and Technology, 2015, 43: 445–453. DOI: 10.1016/j.ast.2015.04.006.
[11]	LIU Y S, WANG Y H, LI Y S, et al. Spectral analysis and self-adjusting mechanism for oscillation phenomenon in hydrogen-oxygen continuously rotating detonation engine [J]. Chinese Journal of Aeronautics, 2015, 28(3): 669–675. DOI: 10.1016/j.cja.2015.03.006.
[12]	XIE Q F, WEN H C, LI W H, et al. Analysis of operating diagram for H₂/Air rotating detonation combustors under lean fuel condition [J]. Energy, 2018, 151: 408–419. DOI: 10.1016/j.energy.2018.03.062.
[13]	LIN W, ZHOU J, LIU S J, et al. Experimental study on propagation mode of H₂/Air continuously rotating detonation wave [J]. International Journal of Hydrogen Energy, 2015, 40(4): 1980–1993. DOI: 10.1016/j.ijhydene.2014.11.119.
[14]	魏万里, 翁春生, 武郁文, 等. 氧化剂喷注面积对连续旋转爆轰波传播特性影响的实验研究 [J]. 兵工学报, 2018, 39(12): 2345–2353. DOI: 10.3969/j.issn.1000-1093.2018.12.008. WEI W L, WENG C S, WU Y W, et al. Experimental research on influence of oxidant injection area on the propagation characteristics of continuous rotating detonation wave [J]. Acta Armamentarii, 2018, 39(12): 2345–2353. DOI: 10.3969/j.issn.1000-1093.2018.12.008.
[15]	DENG L, MA H, XU C, et al. The feasibility of mode control in rotating detonation engine [J]. Applied Thermal Engineering, 2018, 129: 1538–1550. DOI: 10.1016/j.applthermaleng.2017.10.146.
[16]	郑权, 翁春生, 白桥栋. 当量比对液体燃料旋转爆轰发动机爆轰影响实验研究 [J]. 推进技术, 2015, 36(6): 947–952. DOI: 10.13675/j.cnki.tjjs.2015.06.020. ZHENG Q, WENG C S, BAI Q D. Experimental study on effects of equivalence ratio on detonation characteristics of liquid-fueled rotating detonation engine [J]. Journal of Propulsion Technology, 2015, 36(6): 947–952. DOI: 10.13675/j.cnki.tjjs.2015.06.020.
[17]	郑权, 李宝星, 翁春生, 等. 双波对撞模态下的液态燃料旋转爆轰发动机推力测试研究 [J]. 兵工学报, 2017, 38(4): 679–689. DOI: 10.3969/j.issn.1000-1093.2017.04.008. ZHENG Q, LI B X, WENG C S, et al. Thrust measurement of liquid-fueled rotating detonation engine under two-wave collision mode [J]. Acta Armamentarii, 2017, 38(4): 679–689. DOI: 10.3969/j.issn.1000-1093.2017.04.008.
[18]	李宝星, 王中, 许桂阳, 等. 煤油燃料旋转爆轰波起爆与传播特性实验研究 [J]. 兵工学报, 2020, 41(7): 1339–1346. DOI: 10.3969/j.issn.1000-1093.2020.07.011. LI B X, WANG Z, XU G Y, et al. Experimental research on initiation and propagation characteristics of kerosene fuel rotating detonation wave [J]. Acta Armamentarii, 2020, 41(7): 1339–1346. DOI: 10.3969/j.issn.1000-1093.2020.07.011.
[19]	王迪, 周进, 林志勇. 煤油两相连续旋转爆震燃烧室工作特性试验研究 [J]. 推进技术, 2017, 38(2): 471–480. DOI: 10.13675/j.cnki.tjjs.2017.02.028. WANG D, ZHOU J, LIN Z Y. Experimental investigation on operating characteristics of two-phase continuous rotating detonation combustor fueled by kerosene [J]. Journal of Propulsion Technology, 2017, 38(2): 471–480. DOI: 10.13675/j.cnki.tjjs.2017.02.028.