Effect of Particle Injection Velocity on Aluminum Powder / air Two-phase Rotating Detonation Waves

被引：0
|
作者：
Li S. [1 ]
Zhu W. [1 ]
Sun F. [1 ]
Wang Y. [1 ]
Wang J. [2 ]
机构：
[1] College of Mechanical and Electrical Engineering, Beijing University of Chemical Technology, Beijing
[2] College of Engineering, Peking University, Beijing
来源：
Binggong Xuebao/Acta Armamentarii | 2024年 / 45卷 / 04期
关键词：
aluminum powder; gas-solid two-phase flow; particle injection velocity; propagation characteristic; rotating detonation wave;
D O I：
10.12382/bgxb.2022.0895
中图分类号：
学科分类号：
摘要：
The effect of particle injection velocity on the two-phase flow field of a rotating detonation engine fueled by aluminum powder and air is studied. The two-dimensional rotating detonation combustion for the aluminum particles with the injection temperature of 300 K and the high temperature air with the total inflow temperature of 900 K is simulated by using the discrete phase model, one-step surface reaction including kinetic / diffusion-limited rate surface combustion model and multiple-step gas phase decomposition reaction model and considering the devolatilization of incompletely unburned particles. Results show that the particle injection velocity near the inlet is lower than that of air, which results in an incomplete overlap between the air triangle and the particle triangle. As the particle injection velocity increases from 1 m / s to 100 m / s, the detonation velocity and temperature first decreases and then increases. There is a significant temperature difference between particles and air injected into the combustion chamber, which leads to unstable detonation wave propagation. The detonation wave has the best stability when the particle injection velocity is 70 m / s. © 2024 China Ordnance Industry Corporation. All rights reserved.
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页码：1148 / 1157
页数：9
相关论文
共 30 条
  • [1] WEI W L, ZHENG Q, LU J T, Et al., Effect of central cone on working process and performance of liquid-fueled rotating detonation engine, Acta Armamentarii, 42, 6, pp. 1185-1194, (2021)
  • [2] ZHANG S J, ZHANG L F, YAO S B, Et al., Numerical investigation on rotating detonation engine with varying equivalence ratios, Acta Armamentarii, 38, pp. 1-7, (2017)
  • [3] ZHENG Q, LI B X, WENG C S, Et al., Thrust measurement of liquid-fueled rotating detonation engine under two-wave collision mode, Acta Armamentarii, 38, 4, pp. 679-689, (2017)
  • [4] ZHU W C, WANG J P, WANG Y H, Et al., Effect of the air mass flow rate on coal-air two-phase rotating detonation waves, Journal of China Coal Society, 47, 10, pp. 3715-3728, (2022)
  • [5] FROLOV S M, ZVEGINTSEV V I, IVANOVV S, Et al., Hydrogen-fueled detonation ramjet model: wind tunnel tests at approach air stream Mach number 5. 7 and stagnation temperature 1 500 K, International Journal of Hydrogen Energy, 43, 15, pp. 7515-7524, (2018)
  • [6] KAWASAKI A, MATSUYAMA K, MATSUOKA K, Et al., Flight demonstration of detonation engine system using sounding rocket S-520-31: system design, Proceedings of AIAA SciTech Forum, (2022)
  • [7] WANG Y, LE J L, WANG C, Et al., A non-premixed rotating detonation engine using ethylene and air [ J], Applied thermal engineering, 137, pp. 749-757, (2018)
  • [8] FAN L Z, SHI Q, ZHI Y, Et al., Experimental and numerical study on multi-wave modes of H<sub>2</sub> / O<sub>2</sub> rotating detonation combustor, International Journal of Hydrogen Energy, 47, 26, pp. 13121-13133, (2022)
  • [9] BACH E, PASCHEREIT C O, STATHOPOULOS P, Et al., An empirical model for stagnation pressure gain in rotating detonation combustors, Proceedings of the Combustion Institute, 38, 3, pp. 3807-3814, (2021)
  • [10] WANG Y, LE J L., Rotating detonation engines with two fuel orifice schemes, Acta Astronautica, 161, pp. 262-275, (2019)
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