填充流量和当量比对障碍物管道内火焰加速的影响

doi:10.7527/S1000-6893.2024.30940

Abstract

Abstract:

The propagation characteristics of flame in an obstructed tube are crucial to the transition from slow combustion to detonation. To explore the influence of filling flow rate and equivalence ratio on flame acceleration in a rectangular obstructed tube， ethylene was used as fuel， and air was used as oxidant. Based on high-speed schlieren technology and chemiluminescence technology， schlieren images and flame chemiluminescence images with different filling flow rates and equivalence ratios were obtained through experimental research. The experimental results show that the flame propagation in a rectangular channel with obstacles can be divided into two stages： slow acceleration and oscillating acceleration. Moderately increasing the filling flow rate will accelerate the transition from laminar flame to turbulent flame， and significantly promote the flame acceleration process. However， further increasing the filling flow rate will not continuously accelerate the flame propagation， and the maximum flame propagation speed fluctuates in the range of 650 m/s to 700 m/s. When the equivalence ratio of reactants is 1， the flame acceleration effect is obviously better than that of lean or rich conditions. As the filling flow rate increases， the effect of equivalence ratio on flame acceleration gradually weakens.

Key words: detonation, obstacle channel, flame acceleration, filling flow rate, equivalence ratio

CLC Number:

V231.2

Haotian ZHANG, Yonghui ZHANG, Pengfei MA, Yun WANG, Wei FAN. Effects of filling flow rate and equivalence ratio on flame acceleration in an obstacle channel[J]. Acta Aeronautica et Astronautica Sinica, 2025, 46(4): 130940.

Figures/Tables 17

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References 25

1	严传俊，范玮. 燃烧学［M］. 西安：西北工业大学出版社， 2005： 1-2.
	YAN C J， FAN W. Combustion［M］. Xi’an： Northwestern Polytechnical University Press， 2005： 1-2 （in Chinese）.
2	LEE J H S. The detonation phenomenon［M］. Cambridge： Cambridge University Press， 2008： 1-3.
3	KUO K K. Principles of combustion［M］. Hoboken： Wiley-Interscience， 2005： 357-361.
4	严传俊，范玮. 脉冲爆震发动机原理及关键技术［M］. 西安：西北工业大学出版社， 2005： 1-2.
	YAN C J， FAN W. Principle and key technology of pulse detonation engine［M］. Xi’an： Northwestern Polytechnical University Press， 2005： 1-2 （in Chinese）.
5	林伟. 爆震燃烧热射流起爆机理研究［D］. 长沙：国防科技大学， 2010.
	LIN W. Study on initiation mechanism of detonation combustion hot jet［D］. Changsha： National University of Defense Technology， 2010 （in Chinese）.
6	KUZNETSOV M， ALEKSEEV V， MATSUKOV I， et al. DDT in a smooth tube filled with a hydrogen-oxygen mixture［J］. Shock Waves， 2005， 14（3）： 205-215.
7	COATES A M， MATHIAS D L， CANTWELL B J. Numerical investigation of the effect of obstacle shape on deflagration to detonation transition in a hydrogen-air mixture［J］. Combustion and Flame， 2019， 209： 278-290.
8	XIAO H H， ORAN E S. Shock focusing and detonation initiation at a flame front［J］. Combustion and Flame， 2019， 203： 397-406.
9	NEW T， PANICKER P， CHUI K， et al. Experimental study on deflagration-to-detonation transition enhancement methods in a PDE［C］∥Proceedings of the 14th AIAA/AHI Space Planes and Hypersonic Systems and Technologies Conference. Reston： AIAA， 2006.
10	MEYER T， HOKE J， BROWN M， et al. Experimental study of deflagration-to-detonation enhancement techniques in a H2/air pulsed-detonation engine［C］∥38th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. Reston： AIAA， 2002.
11	LEE S Y， WATTS J， SARETTO S， et al. Deflagration to detonation transition processes by turbulence-generating obstacles in pulse detonation engines［J］. Journal of Propulsion and Power， 2004， 20（6）： 1026-1036.
12	JOHANSEN C， CICCARELLI G. Visualization of the unburned gas flow field ahead of an accelerating flame in an obstructed square channel［J］. Combustion and Flame， 2009， 156（2）： 405-416.
13	JOHANSEN C， CICCARELLI G. Numerical simulations of the flow field ahead of an accelerating flame in an obstructed channel［J］. Combustion Theory and Modelling， 2010， 14（2）： 235-255.
14	DEAN A. A review of PDE development for propulsion applications［C］∥45th AIAA Aerospace Sciences Meeting and Exhibit. Reston： AIAA， 2007.
15	CHAPIN D， TANGIRALA V， RASHEED A， et al. Detonation initiation in moving ethylene-air mixtures at elevated temperature and pressure［C］∥42nd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. Reston： AIAA， 2006.
16	GRAY J A， MOECK J P， PASCHEREIT C O. Effect of initial flow velocity on the flame propagation in obstructed channels［C］∥53rd AIAA Aerospace Sciences Meeting. Reston： AIAA， 2015.
17	张永辉，张启斌，赵明皓，等. 混合物填充速度对火焰加速及DDT转变特性实验［J］. 航空动力学报， 2024， 39 （9）： 263-272.
	ZHANG Y H， ZHANG Q B， ZHAO M H， et al. Experimental study on the effect of mixture filling rate on flame acceleration and DDT transition characteristics［J］. Journal of Aerospace Power， 2024， 39 （9）： 263-272 （in Chinese）.
18	WANG Y， DONG R X， SHEN S， et al. Effect of fill flow rate on flame acceleration in a detonation channel［J］. Aerospace Science and Technology， 2021， 117： 106936.
19	DAYMA G， HALTER F， DAGAUT P. New insights into the peculiar behavior of laminar burning velocities of hydrogen-air flames according to pressure and equivalence ratio［J］. Combustion and Flame， 2014， 161（9）： 2235-2241.
20	KAMAL M M， BARLOW R S， HOCHGREB S. Conditional analysis of turbulent premixed and stratified flames on local equivalence ratio and progress of reaction［J］. Combustion and Flame， 2015， 162（10）： 3896-3913.
21	NGUYEN V B， LI J M， CHANG P H， et al. Effect of ethylene fuel/air equivalence ratio on the dynamics of deflagration-to-detonation transition and detonation propagation process［J］. Combustion Science and Technology， 2018， 190（9）： 1630-1658.
22	何建男. 微尺度爆震燃烧的基础研究与微动力推进的初步探索［D］. 西安：西北工业大学， 2018.
	HE J N. Basic research on micro-scale detonation combustion and preliminary exploration of micro-power propulsion［D］. Xi’an： Northwestern Polytechnical University， 2018 （in Chinese）.
23	LANDAU L. On the theory of slow combustion［M］∥Dynamics of Curved Fronts. Amsterdam： Elsevier， 1988： 403-411.
24	JOULIN G， CLAVIN P. Linear stability analysis of nonadiabatic flames： Diffusional-thermal model［J］. Combustion and Flame， 1979， 35： 139-153.
25	SIVASHINSKY G I. Diffusional-thermal theory of cellular flames［J］. Combustion Science and Technology， 1977， 15（3-4）： 137-145.

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Effects of filling flow rate and equivalence ratio on flame acceleration in an obstacle channel

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