Numerical simulations on effect of equivalence ratio on flow field in aluminum power/air rotating detonation engines

被引：0

作者：

Li S. ^{[1
]}

Yang F. ^{[1
]}

Wang Y. ^{[1
]}

Wang J. ^{[2
]}

Zhang G. ^{[3
]}

机构：

[1] College of Mechanical and Electrical Engineering, Beijing University of Chemical Technology, Beijing

[2] College of Engineering, Peking University, Beijing

[3] School of Aerospace Engineering, Beijing Institute of Technology, Beijing

来源：

Hangkong Dongli Xuebao/Journal of Aerospace Power | 2024年 / 39卷 / 05期

关键词：

aluminum powder; deflagration; equivalence ratio; gas-solid two-phase flow; rotating detonation engine;

D O I：

10.13224/j.cnki.jasp.20210560

中图分类号：

学科分类号：

摘要：

The flow field of a gas-solid two-phase rotating detonation engine taking aluminum powder as fuel and air as oxidant with one step reaction was investigated by two-dimensional numerical simulations at different equivalence ratios. Results showed that the velocity of the detonation wave decreased from 2 070 m/s to 1 690 m/s and detonation pressure decreased from 5.67 MPa to 4.87 MPa when the equivalence ratio increased from 0.6 to 1.4, because the average local equivalence ratio increased from 0.929 to 2.093, which was caused by incomplete overlapping of trigonal zones between air and particles because of the injection velocity difference between air and particles. The flow field was similar to that in gas phase rotating detonation engines. However, unique distribution characteristics, including two particle groups, four particle bands and gaps among them due to the interaction between gas phase and solid phase, were obtained. © 2024 Beijing University of Aeronautics and Astronautics (BUAA). All rights reserved.

引用

共 36 条

[1] FALEMPIN F，, LE NAOUR B., R&T effort on pulsed and continuous detonation wave engines, (2009)
[2] WANG Bing, XIE Qiaofeng, WEN Haocheng, Et al., Research progress of detonation engines, Journal of Propulsion Technology, 42, 4, pp. 721-737, (2021)
[3] VOITSEKHOVSKII B V., Stationary spin detonation, Journal of Applied Mechanics and Technical Physics, 3, pp. 157-164, (1960)
[4] FOTIA M, KAEMMING T A, Et al., Study of the experimental performance of a rotating detonation engine with nozzled exhaust flow, (2015)
[5] FOTIA M，, SCHAUER F，, HOKE J., Experimental study of performance scaling in rotating detonation engines operated on hydrogen and gaseous hydrocarbon fuel, (2015)
[6] SONWANE C，, CLAFLIN S, Et al., Recent advances in power cycles using rotating detonation engines with subcritical and supercritical CO<sub>2</sub>, Power Cycles, (2014)
[7] CLAFLIN S., Recent progress in continuous detonation engine development at pratt & whitney rocketdyne, (2012)
[8] ANDERSON W，, HEISTER S D，, HARTSFIELD C., Experimental study of a hypergolically ignited liquid bipropellant rotating detonation rocket engine, (2019)
[9] ZHU Yiyuan, WANG Ke, WANG Zhicheng, Et al., Study on the performance of a rotating detonation chamber with different aerospike nozzles[J], Aerospace Science and Technology, 107, (2020)
[10] LIU Qian, ZHENG Hongtao, LI Zhiming, Et al., Performance of continuously rotating detonation combustor, Journal of Aerospace Power, 30, 6, pp. 1328-1336, (2015)

← 1 2 3 4 →