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On-line Access: 2024-08-27

Received: 2023-10-17

Revision Accepted: 2024-05-08

Crosschecked: 2021-06-23

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Citations:  Bibtex RefMan EndNote GB/T7714

 ORCID:

Wei-jie Fan

https://orcid.org/0000-0002-4766-5494

Jin Zhou

https://orcid.org/0000-0002-0563-4411

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Journal of Zhejiang University SCIENCE A 2021 Vol.22 No.7 P.547-563

http://doi.org/10.1631/jzus.A2000314


Effects of the geometrical parameters of the injection nozzle on ethylene-air continuous rotating detonation


Author(s):  Wei-jie Fan, Jin Zhou, Shi-jie Liu, Hao-yang Peng

Affiliation(s):  Science and Technology on Scramjet Laboratory, College of Aerospace Science and Technology, National University of Defense Technology, Changsha 410073, China

Corresponding email(s):   zj706@vip.sina.com

Key Words:  Continuous rotating detonation (CRD), Ethylene-air, Injection nozzle, Feedback pressure


Wei-jie Fan, Jin Zhou, Shi-jie Liu, Hao-yang Peng. Effects of the geometrical parameters of the injection nozzle on ethylene-air continuous rotating detonation[J]. Journal of Zhejiang University Science A, 2021, 22(7): 547-563.

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T1 - Effects of the geometrical parameters of the injection nozzle on ethylene-air continuous rotating detonation
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DOI - 10.1631/jzus.A2000314


Abstract: 
Compared with traditional isobaric combustion, continuous rotating detonation (CRD) has been theoretically proved to be a more efficient combustion mode with higher thermal cycle efficiency. However, the realization and stable operating of liquid kerosene detonation is still a challenge. As a major component of kerosene pyrolysis products after regenerative cooling, ethylene is a transitional hydrocarbon fuel from kerosene to hydrogen and it is worth studying. In this paper, a series of 2D numerical simulations are conducted to investigate the effects of the injection nozzle on the ethylene-air CRD. Three geometrical parameters of the nozzle are thoroughly tested including the distance between two neighboring nozzle centers, the nozzle exit width, and the slant angle of the nozzle. The results show that an ethylene-air detonation wave is realized and it propagates stably. A small distance between two neighboring nozzle centers is conducive to improving the strength of the CRD wave and leads to greater feedback pressure into the plenum. As the nozzle exit width increases, the strength of the CRD wave and the feedback pressure into the plenum both increase. The CRD wave propagation velocity is greatly improved and the feedback pressure into the plenum is significantly reduced when the slant angle of the nozzle is positive. By contrast, a sizeable reduction in velocity is found when the angle is negative. The co-rotating two-wave propagation mode is observed when the angle is 30°, and the highest CRD propagation velocity and the lowest feedback pressure are both obtained when the angle is 60°.

喷孔几何参数对乙烯-空气连续旋转爆震波传播特性的影响

目的:通过数值模拟分析乙烯-空气连续旋转爆震波的流场特征,探讨喷孔几何参数(喷孔间距、喷孔出口宽度和喷孔倾斜角)对乙烯-空气连续旋转爆震波传播特性的影响,为降低乙烯-空气连续旋转爆震波传播速度亏损及爆震波对上游积气腔的反馈压力提供一些设计思路.
创新点:1. 采用含积气腔和喷孔的喷注模型进行乙烯-空气连续旋转爆震波的数值仿真,观察到了爆震波的模态转换过程并定量分析了爆震波对积气腔的反馈压力;2. 通过改变喷孔的倾斜角,在提高爆震波传播速度的同时减小了积气腔内的反馈压力.
方法:1. 通过FLUENT进行数值仿真,分析乙烯-空气连续旋转爆震波的基本流场结构(图7和9)和爆震波传播模态的转换过程(图17).2. 通过在积气腔和燃烧室内设置压力监测点,得到积气腔和燃烧室内的压力记录曲线(图8、10、13、14、18和20);通过压力曲线,计算爆震波的平均传播速度和积气腔内压力的相对标准差.3. 通过对比分析,总结喷孔几何参数对爆震波传播速度和积气腔内反馈压力的影响(图11、15和19).
结论:1. 喷孔间距对连续旋转爆震波的强度和积气腔的反馈压力都有影响;较小的喷孔间距有助于提高爆震波的强度,但也会引起积气腔内更高的反馈压力.2. 随着喷孔出口宽度的增大,爆震波的强度增强,也使积气腔内的反馈压力显著增加.3. 喷孔倾斜角对爆震波的传播特性和积气腔内的反馈压力有重要影响:当喷孔沿爆震波传播方向倾斜时,爆震波的传播速度明显提高;反之,爆震波的传播速度明显降低.采用倾斜喷注时,积气腔内的反馈压力显著降低,并且喷管倾斜程度越大,积气腔内的压力越稳定.4. 倾斜喷注可以引起爆震波传播模态的转变;当倾斜角为30°时,出现了同向双波传播模态.5. 预着火产生的热点和预混气沿爆震波传播方向的分速度有利于形成新的爆震波.

关键词:连续旋转爆震波;乙烯-空气组合;喷孔;反馈压力

Darkslateblue:Affiliate; Royal Blue:Author; Turquoise:Article

Reference

[1]Anand V, George ACS, Driscoll RB, et al., 2015. Statistical treatment of wave instability in rotating detonation combustors. Proceedings of the 53rd AIAA Aerospace Sciences Meeting.

[2]Anand V, George AS, Driscoll R, et al., 2016a. Analysis of air inlet and fuel plenum behavior in a rotating detonation combustor. Experimental Thermal and Fluid Science, 70:408-416.

[3]Anand V, George AS, Driscoll R, et al., 2016b. Investigation of rotating detonation combustor operation with H2-air mixtures. International Journal of Hydrogen Energy, 41(2):1281-1292.

[4]Bykovskii FA, Vedernikov EF, 1996. Self-sustaining pulsating detonation of gas-mixture flow. Combustion, Explosion and Shock Waves, 32(4):442-448.

[5]Cai XD, Liang JH, Deiterding R, et al., 2016. Adaptive mesh refinement based simulations of three-dimensional detonation combustion in supersonic combustible mixtures with a detailed reaction model. International Journal of Hydrogen Energy, 41(4):3222-3239.

[6]Davidenko DM, Gökalp I, Kudryavtsev AN, 2007. Numerical simulation of the continuous rotating hydrogen-oxygen detonation with a detailed chemical mechanism. West-east High Speed Flow Field Conference, p.19-22.

[7]Driscoll R, George AS, Gutmark EJ, 2016. Numerical investigation of injection within an axisymmetric rotating detonation engine. International Journal of Hydrogen Energy, 41(3):2052-2063.

[8]Frolov SM, Dubrovskii AV, Ivanov VS, et al., 2013. Three-dimensional numerical simulation of the operation of a rotating-detonation chamber with separate supply of fuel and oxidizer. Russian Journal of Physical Chemistry B, 7(1):35-43.

[9]Fujii J, Kumazawa Y, Matsuo A, et al., 2016. Numerical investigation on detonation velocity in rotating detonation engine chamber. Proceedings of the Combustion Institute, 36(2):2665-2672.

[10]Gaillard T, Davidenko D, Dupoirieux F, 2017. Numerical simulation of a rotating detonation with a realistic injector designed for separate supply of gaseous hydrogen and oxygen. Acta Astronautica, 141:64-78.

[11]Hishida M, Fujiwara T, Wolanski P, 2009. Fundamentals of rotating detonations. Shock Waves, 19(1):1-10.

[12]Huang SY, Zhou J, Liu SJ, et al., 2019. Effects of pintle injector on ethylene-air rocket-based continuous rotating detonation. Acta Astronautica, 164:311-320.

[13]Huang W, Chang JT, Yan L, 2020. Mixing and combustion in supersonic/hypersonic flows. Journal of Zhejiang University-SCIENCE A (Applied Physics & Engineering), 21(8):609-613.

[14]Kindracki J, Wolański P, Gut Z, et al., 2011. Experimental research on the rotating detonation in gaseous fuels– oxygen mixtures. Shock Waves, 21(2):75-84.

[15]Lei ZD, Chen ZW, Yang XQ, et al., 2020a. Operational mode transition in a rotating detonation engine. Journal of Zhejiang University-SCIENCE A (Applied Physics & Engineering), 21(9):721-733.

[16]Lei ZD, Yang XQ, Ding J, et al., 2020b. Performance of rotating detonation engine with stratified injection. Journal of Zhejiang University-SCIENCE A (Applied Physics & Engineering), 21(9):734-744.

[17]Li BX, Wu YW, Weng CS, et al., 2018. Influence of equivalence ratio on the propagation characteristics of rotating detonation wave. Experimental Thermal and Fluid Science, 93:366-378.

[18]Lin W, Zhou J, Liu SJ, et al., 2015. Experimental study on propagation mode of H2/air continuously rotating detonation wave. International Journal of Hydrogen Energy, 40(4):1980-1993.

[19]Liu M, Zhou R, Wang JP, 2015. Numerical investigation of different injection patterns in rotating detonation engines. Combustion Science and Technology, 187(3):343-361.

[20]Liu SJ, Lin ZY, Sun MB, et al., 2011. Thrust vectoring of a continuous rotating detonation engine by changing the local injection pressure. Chinese Physics Letters, 28(9):094704.

[21]Liu SJ, Peng HY, Liu WD, et al., 2020. Effects of cavity depth on the ethylene-air continuous rotating detonation. Acta Astronautica, 166:1-10.

[22]Liu YS, Wang YH, Li YS, et al., 2015. Spectral analysis and self-adjusting mechanism for oscillation phenomenon in hydrogen-oxygen continuously rotating detonation engine. Chinese Journal of Aeronautics, 28(3):669-675.

[23]Meng QY, Zhao NB, Zheng HT, et al., 2018. Numerical investigation of the effect of inlet mass flow rates on H2/air non-premixed rotating detonation wave. International Journal of Hydrogen Energy, 43(29):13618-13631.

[24]Morris C, 2005. Axisymmetric modeling of pulse detonation rocket engines. Proceedings of the 41st AIAA/ASME/ SAE/ASEE Joint Propulsion Conference & Exhibit.

[25]Naples A, Hoke J, Schauer F, 2015. Experimental investigation of a rotating detonation engine injector temporal response. Proceedings of the 53rd AIAA Aerospace Sciences Meeting.

[26]Nicholls JA, Cullen RE, Ragland KW, 1966. Feasibility studies of a rotating detonation wave rocket motor. Journal of Spacecraft and Rockets, 3(6):893-898.

[27]Nikitin VF, Dushin VR, Phylippov YG, et al., 2009. Pulse detonation engines: technical approaches. Acta Astronautica, 64(2-3):281-287.

[28]Nordeen CA, Schwer D, Schauer F, et al., 2016. Role of inlet reactant mixedness on the thermodynamic performance of a rotating detonation engine. Shock Waves, 26(4):417-428.

[29]Peng HY, Liu WD, Liu SJ, et al., 2019a. The effect of cavity on ethylene-air continuous rotating detonation in the annular combustor. International Journal of Hydrogen Energy, 44(26):14032-14043.

[30]Peng HY, Liu WD, Liu SJ, et al., 2019b. Realization of methane-air continuous rotating detonation wave. Acta Astronautica, 164:1-8.

[31]Rankin BA, Fotia M, Paxson DE, et al., 2015. Experimental and numerical evaluation of pressure gain combustion in a rotating detonation engine. Proceedings of the 53rd AIAA Aerospace Sciences Meeting.

[32]Schwer D, Kailasanath K, 2011. Numerical study of the effects of engine size on rotating detonation engines. Proceedings of the 49th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition.

[33]Schwer D, Kailasanath K, 2012. Feedback into mixture plenums in rotating detonation engines. Proceedings of the 50th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition.

[34]Schwer D, Kailasanath K, 2013. Fluid dynamics of rotating detonation engines with hydrogen and hydrocarbon fuels. Proceedings of the Combustion Institute, 34(2):1991-1998.

[35]Schwer D, Corrigan A, Taylor B, et al., 2013. On reducing feedback pressure in rotating detonation engines. Proceedings of the 51st AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition.

[36]Shao YT, Liu M, Wang JP, et al., 2010. Numerical investigation of rotating detonation engine propulsive performance. Combustion Science and Technology, 182(11-12):1586-1597.

[37]Shi W, Tian Y, Zhang WZ, et al., 2020. Experimental investigation on flame stabilization of a kerosene-fueled scramjet combustor with pilot hydrogen. Journal of Zhejiang University-SCIENCE A (Applied Physics & Engineering), 21(8):663-672.

[38]Singh DJ, Jachimowski CJ, 1994. Quasiglobal reaction model for ethylene combustion. AIAA Journal, 32(1):213-216.

[39]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.

[40]Smirnov NN, Nikitin VF, Stamov LI, et al., 2018. Rotating detonation in a ramjet engine three-dimensional modeling. Aerospace Science and Technology, 81:213-224.

[41]Stewart DS, Kasimov AR, 2006. State of detonation stability theory and its application to propulsion. Journal of Propulsion and Power, 22(6):1230-1244.

[42]Sun J, Zhou J, Liu SJ, et al., 2017. Effects of injection nozzle exit width on rotating detonation engine. Acta Astronautica, 140:388-401.

[43]Sun J, Zhou J, Liu SJ, et al., 2018a. Numerical investigation of a rotating detonation engine under premixed/non-premixed conditions. Acta Astronautica, 152:630-638.

[44]Sun J, Zhou J, Liu SJ, et al., 2018b. Plume flowfield and propulsive performance analysis of a rotating detonation engine. Aerospace Science and Technology, 81:383-393.

[45]Sun J, Zhou J, Liu SJ, et al., 2019. Effects of air injection throat width on a non-premixed rotating detonation engine. Acta Astronautica, 159:189-198.

[46]Sun YC, Cai Z, Wang TY, et al., 2020. Numerical study on cavity ignition process in a supersonic combustor. Journal of Zhejiang University-SCIENCE A (Applied Physics & Engineering), 21(10):848-858.

[47]Taki S, Fujiwara T, 1978. Numerical analysis of two-dimensional nonsteady detonations. AIAA Journal, 16(1):73-77.

[48]Voitsekhovskii BV, 1959. Stationary spin detonation. Doklady Akademii Nayk USSR, 129(6):1254-1256.

[49]Wang P, Shen CB, 2019. Characteristics of mixing enhancement achieved using a pulsed plasma synthetic jet in a supersonic flow. Journal of Zhejiang University-SCIENCE A (Applied Physics & Engineering), 20(9):701-713.

[50]Wang YH, Le JL, Wang C, et al., 2018. A non-premixed rotating detonation engine using ethylene and air. Applied Thermal Engineering, 137:749-757.

[51]Xie QF, Wen HC, Li WH, et al., 2018. Analysis of operating diagram for H2/air rotating detonation combustors under lean fuel condition. Energy, 151:408-419.

[52]Yao S, Han X, Liu Y, et al., 2017. Numerical study of rotating detonation engine with an array of injection holes. Shock Waves, 27(3):467-476.

[53]Zhdan SA, 2008. Mathematical model of continuous detonation in an annular combustor with a supersonic flow velocity. Combustion, Explosion, and Shock Waves, 44(6):690-697.

[54]Zhdan SA, Mardashev AM, Mitrofanov VV, 1990. Calculation of the flow of spin detonation in an annular chamber. Combustion, Explosion and Shock Waves, 26(2):210-214.

[55]Zhdan SA, Bykovskii FA, Vedernikov EF, 2007. Mathematical modeling of a rotating detonation wave in a hydrogen-oxygen mixture. Combustion, Explosion, and Shock Waves, 43(4):449-459.

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