调控燃烧室燃料初始分布建立稳定旋转爆轰波的方法

雷知迪; 陈正武; 杨小权; 李孝伟; 丁珏; 翁培奋

doi:10.11883/bzycj-2018-0208

调控燃烧室燃料初始分布建立稳定旋转爆轰波的方法

doi: 10.11883/bzycj-2018-0208

雷知迪^{1, 3,},
陈正武²,
杨小权^{1, 3},
李孝伟^{1, 3, ,},
丁珏^{1, 3},
翁培奋^{1, 3}

1.
上海大学上海市应用数学和力学研究所，上海 200072
2.
中国空气动力研究与发展中心气动噪声控制重点实验室，四川绵阳 621000
3.
上海大学现代飞行器空气动力学研究中心，上海 200072

基金项目: 国家自然科学基金(11472167，11702329)；气动噪声控制重点实验室开放课题(ANCL20180103)

详细信息

作者简介:
雷知迪（1987－　），男，博士，zhidi_lei@163.com

通讯作者:
李孝伟（1969－　），男，博士，副教授，xwli@staff.shu.edu.cn

中图分类号: O389
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- 被引次数: 0
出版历程
- 收稿日期: 2018-06-12
- 修回日期: 2019-04-22
- 刊出日期: 2019-09-01

Method based on controlling initial fuel distribution to establish stable rotating detonation wave in combustion chamber

LEI Zhidi^{1, 3
,},
CHEN Zhengwu²,
YANG Xiaoquan^{1, 3},
LI Xiaowei^{1, 3
, ,},
DING Jue^{1, 3},
WENG Peifen^{1, 3}

1.
Shanghai Institute of Applied Mathematics and Mechanics, Shanghai University, Shanghai 200072, China
2.
Key Laboratory of Aerodynamic Noise Control, China Aerodynamics Research and Development Center, Mianyang 621000, Sichuan, China
3.
Modern Aircraft Aerodynamics Research Center of Shanghai University, Shanghai 200072, China

摘要

摘要: 旋转爆轰发动机具有比传统航空航天发动机更高的燃烧效率，近年来引起人们的关注。其中，点火启动过程尤为重要。为达到一次点火就能在燃烧室内建立稳定旋转爆轰波的目的，本文提出通过控制点火前燃料初始分布来建立稳定旋转爆轰波的方法，并基于纳维-斯托克斯方程与10组分27可逆反应基元化学反应模型的数值模拟验证了该方法的可行性。对旋转爆轰波传播特性的研究表明，燃料在发动机燃烧室中的分布是影响旋转爆轰波建立的关键。在燃料喷注压力较低时此影响尤为明显，它决定了爆轰波发展第一周期内波前燃料层厚度。而波前燃料层与波的稳定传播密切相关。基于该方法，本文对燃烧室初始流速为360 m/s，喷注总压0.4 MPa的旋转爆轰发动机实现了点火至稳定爆轰，得到的爆轰波传播平均速度为1 604 m/s，频率为5 347.6 Hz。此外，燃料初始填充率作为燃料初始分布的量化指标，文中给出了它建立稳定旋转爆轰时的临界范围。
- 旋转爆轰发动机 /
- 起爆方法 /
- 燃料初始分布 /
- 燃料喷注压力 /
- 爆轰稳定性
Abstract: In recent years, Rotary Detonation Engine (RDE) has attracted more and more attention because of their higher combustion efficiency than conventional aerospace engines. For the key problems, ignition technique is particularly important. In order to establish a steady rotating detonation wave under one single ignition in a combustion chamber, a method based on controlling initial fuel distribution is proposed to start a rotating detonation engine under 0.4 MPa injection total pressure using hydrogen/air mixture as its propellant. Two-dimensional reactive Navier-Stokes equation coupled with the Arrhenius kinetic model and κ-ε model are used to simulate detonation process. Elementary chemical reaction model with 9 species 27 reversible reactions is applied to describe the evolution of reaction components. The finite volume method is conducted, and flux terms are solved by using the monotonic upstream-centered scheme for conservation laws, and the time integration is performed by using Euler method. Grid numbers are 600 (azimuthal direction) ×200 (axial direction), with mesh size of about 0.5 mm. Initial fuel filling rate (ϕ) is used to quantify the initial fuel distribution. The numerical study on the propagation characteristics of rotating detonation wave shows that the initial fuel filling rate is the key to the establishment of rotary detonation wave. This effect is particularly evident when the fuel injection pressure is low, which determines the height of the fuel layer(h_f) for the first cycle of detonation wave development. When RDE operating steadily, h_f is a function of the mixture sensitivity to detonation. But in initial stage, h_f is affected by the fuel distribution and this affection can last more than one period. Once detonation wave or deflagration wave formed, it can either maintain rotating or die down, which is determined by the height of mixture layer ahead of it. Thus, keeping h_f in an appropriate range by adjusting the initial fuel filling rate is the key to establish and maintain a rotating detonation wave in initial stage. Also, in this stage DW faces maximum possibility of extinguish. Based on this strategy, a rotating detonation wave is established successfully in combustion chamber with diameter of 95.5 mm and the length of chamber is 100 mm. The computed results give the rotating detonation wave has a velocity of 1 604 m/s and operational frequency is 5347.6 Hz. Furthermore, there are four operation modes of the engine due to different initial fuel filling rate, which are failed initiation of the detonation (0%−13.3%), stable rotating detonation (13.3%−20%), unstable detonation (20%−26.6%) and dying detonation (26.7%−100%). So the critical range of the initial fuel filling rate for steady rotating detonation is obtained. Moreover, the initial fuel distribution also influences the delay time of fuel deflagration to detonation transition.
- rotating detonation engine /
- ignition technique /
- fuel initial distribution /
- fuel injection pressure /
- detonation stability

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图 1 RDE燃烧室示意图

Figure 1. Schematic diagram of combustion chamber

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图 2 计算域和燃料的初始分布

Figure 2. Computational domain and fuel initial distribution

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图 3 ϕ=20%时x=160 mm，y=85 mm处的压力和温度随时间的变化曲线

Figure 3. Pressure and temperature versus time (x=160 mm, y=85 mm, ϕ=20%)

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图 4 入口界面燃料的注入速度(t=200 μs)

Figure 4. Injection velocity at inlet (t=200 μs)

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图 5 $\phi $ =20%，$\phi $66.7%燃料的积累(t=230 μs)

Figure 5. Fuel distribution for different initial fuel filling rates (t=230 μs)

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图 6 燃料H₂质量分数(${Y_{{{\rm{H}}_{\rm{2}}}}}$)云图

Figure 6. Mass fraction of H₂ (${Y_{{{\rm{H}}_{\rm{2}}}}}$) contours

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图 7 波前燃料层厚度随时间变化

Figure 7. The height of the fuel layer versus time

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图 8 t=280 μs、流场温度云图，爆轰波从左往右传播

Figure 8. Temperature contours, detonation wave propagates from left to right (Case C, t=280 μs)

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图 9 280、300、320、380 μs时刻入口界面处压强曲线

Figure 9. Pressure distribution at t=280 μs, 300 μs, 320 μs, 380 μs

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图 10 燃料初始填充率、波前燃料层厚度和爆轰波稳定性之间的相互影响

Figure 10. Schematic of the relationship between initial fuel filling rate, fuel layer height ahead of detonation wave and stability of detonation wave

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表 1 氢气、氧气、氮气混合气体10组分27个可逆反应的化学反应机理

Table 1. Chemical reaction mechanisms

反应序号	反应式	反应序号	反应式
1	2O+M↔O₂+M	15	H+HO₂↔O₂+H₂
2	O+H+M↔OH+M	16	H+HO₂↔2OH
3	O+H₂↔H+OH	17	H+H₂O₂↔HO₂+H₂
4	O+HO₂↔OH+O₂	18	H+H₂O₂↔OH+H₂O
5	O+H₂O₂↔OH+HO₂	19	OH+H₂↔H+H₂O
6	H+2O₂↔HO₂+O₂	20	2OH(+M)↔H₂O₂(+M)
7	H+O₂+H₂O↔HO₂+H₂O	21	2OH↔O+H₂O
8	H+O₂+AR↔HO₂+AR	22	OH+HO₂↔O₂+H₂O
9	H+O₂↔O+OH	23	OH+HO₂↔O₂+H₂O
10	2H+M↔H₂+M	24	OH+HO₂↔O₂+H₂O
11	2H+H₂↔2H₂	25	2HO₂↔O₂+H₂O₂
12	2H+H₂O↔H₂+H₂O	26	2HO₂↔O₂+H₂O₂
13	2H+H₂O↔H₂+H₂O	27	OH+HO₂↔O₂+H₂O
14	H+HO₂↔O+H₂O

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表 2 不同初始填充率下点火结果

Table 2. Operation modes of the engine at different initial fuel filling rate

网格尺寸/mm	爆轰波波速/(m∙s⁻¹)	C-J 压力/MPa
理论值	1 976.5	1.61
实验值	1 970.0	−
0.5	1 954.5	1.63
1	1 963.6	1.54
2	1 982.0	1.50

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表 3 不同初始填充率下点火结果

Table 3. Operation modes of the engine at different initial fuel filling rate

ϕ	d/mm	点火结果
0%～13.3%	0～40	未形成爆轰波
13.4%～20%	40.2～60	稳定旋转爆轰
21%～26.6%	63～79.8	不稳定的旋转爆轰
26.7%～100%	80.1～300	爆轰波熄灭

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参考文献(21)

[1]	VOITSEKHOVSKII B V. Stationary spin detonation [J]. Doklady Akademii Nauk Sssr, 1959, 129(6): 1254–1256.
[2]	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.
[3]	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.
[4]	BYKOVSKII F A, VEDERNIKOV E F. Continuous detonation of a subsonic flow of a propellant [J]. Combustion, Explosion and Shock Waves, 2003, 39(3): 323–334. DOI: 10.1023/A:102380052.
[5]	NICHOLLS J A, CULLEN R E, RAGLAND K W. Feasibility studies of a rotating detonation wave rocket motor [J]. Journal of Spacecraft and Rockets, 1966, 3(6): 893–898. DOI: 10.2514/3.28557.
[6]	KINDRACKI J, WOLANSKI P, GUT Z. Experimental research on the rotating detonation in gaseous fuels–oxygen mixtures [J]. Shock Waves, 2011, 21(2): 75–84. DOI: 10.1007/s00193-011-0298-y.
[7]	YANG C, WU X, MA H, et al. Experimental research on initiation characteristics of a rotating detonation engine [J]. Experimental Thermal and Fluid Science, 2016, 71: 154–163. DOI: 10.1016/j.expthermflusci.2015.10.019.
[8]	SHAO Y, LIU M, WANG J. Continuous detonation engine and effects of different types of nozzle on its propulsion performance [J]. Chinese Journal of Aeronautics, 2010, 23(6): 647–652. DOI: 10.1016/S1000-9361(09)60266-1.
[9]	YAO S, WANG J. Multiple ignitions and the stability of rotating detonation waves [J]. Applied Thermal Engineering, 2016, 108(5): 927–936. DOI: 10.1016/j.applthermaleng.2016.07.166.
[10]	李宝星, 翁春生. 进气总压对连续旋转爆轰发动机爆轰影响的二维数值模拟 [J]. 固体火箭技术, 2016(5): 612–618. DOI: 10.7673/j.issn.1006-2793.2016.05.003. LI Baoxing, WENG Chunsheng. Two-dimensional numerical simulation of the inlet stagnation pressure influence on the continuous rotating detonation engine [J]. Journal of Solid Rocket Technology, 2016(5): 612–618. DOI: 10.7673/j.issn.1006-2793.2016.05.003.
[11]	HIPPLER H. Shock wave studies of the reactions, HO+H₂O₂→H₂O+HO₂ and HO+HO₂→H₂O+O₂ between 930 and 1680 K [J]. The Journal of Chemical Physics, 1995, 103(9): 3510. DOI: 10.1063/1.470235.
[12]	MARINOV N, WESTBROOK C K, PITZ W. Detailed and global chemical kinetics model for hydrogen [C] // Chan S H. Transport Phenomena in Combustion. USA: Taylor & Francis, 1995: 118−129.
[13]	FUJII J, KUMAZAWA Y, Matsuo A, et al. Numerical investigation on detonation velocity in rotating detonation engine chamber [J]. Proceedings of the Combustion Institute, 2017, 36(2): 2665–2672. DOI: 10.1016/j.proci.2016.06.155.
[14]	SCHWER, D, KAILASANATH, K. Numerical investigation of the physics of rotating-detonation-engines [J]. Proceedings of the Combustion Institute, 2011, 33(2): 2195–2202. DOI: 10.1016/j.proci.2010.07.050.
[15]	GAMEZO V N, DESBORDES D, Oran E S. Two-dimensional reactive flow dynamics in cellular detonation waves [J]. Shock Waves, 1999, 9(1): 11–17. DOI: 10.1007/s001930050134.
[16]	YI T H, ANDERSON D, WILSON D, et al. Numerical study of two-dimensional viscous, chemically reacting flow: AIAA 2005-4868[R]. USA: NASA, 2005. DOI: 10.2514/6.2005-4868.
[17]	DEND 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.
[18]	GINSBERG T, CICCARELLI G, BOCCIO J. Initial hydrogen detonation data from the high-temperature combustion facility: NUREG/CP—0139 [R]. Austria: INIS, 1994.
[19]	KINDRACKI J. Analysis of the experimental results of the initiation of detonation in short tubes with kerosene–oxidizer mixtures [J]. Journal of Loss Prevention in the Process Industries, 2013, 26(6): 1515–1523. DOI: 10.1016/j.jlp.2013.09.003.
[20]	BYKOVSKII F A and MITROFANOV V V. Detonation combustion of a gas mixture in a cylindrical chamber [J]. Combustion, Explosion & Shock Waves, 1980, 16(5): 570–578. DOI: 10.1007/BF00794937.
[21]	VASIL'EV A A and Zak D V. Detonation of gas jets [J]. Combustion, Explosion, and Shock Waves, 1986, 22(4): 463–468. DOI: 10.1007/BF00862893.