Numerical investigation of mode transition and hysteresis in a cavity-based dual-mode scramjet combustor

doi:10.1016/j.ast.2019.105420

	Numerical investigation of mode transition and hysteresis in a cavity-based dual-mode scramjet combustor
	Zhang X(张旭)1,2; Yue LJ(岳连捷)1,2 ; Huang TL(黄庭隆)1,2; Zhang QF(张启帆)1,2 ; Zhang XY(张新宇)1,2
通讯作者	Yue, Lianjie(yuelj@imech.ac.cn)
发表期刊	AEROSPACE SCIENCE AND TECHNOLOGY
	2019-11-01
卷号	94 页码:10
ISSN	1270-9638
摘要	The effect of ethylene fuel equivalence ratio (ER) variation directions on combustion states in a dual-mode scramjet combustor was numerically investigated. The combustor employed transverse wall fuel injectors and downstream cavity flameholders without pilot fuel, which are fundamental components in many practical combustors. The isolator inflow Mach number was 3.1, and static pressure, stagnation pressure and stagnation temperature were 53 kPa, 2622 kPa and 1656 K, respectively. The ER was regulated abruptly in a piecewise constant manner, from 0.10 to 1.02, and then back to 0.10. A 3-D URANS method with a recognized two-step kinetics model was adopted. Results exhibited two combustion hysteresis loops, which indicated that different types of combustion mode transitions could result in hysteresis. The first was a hysteretic phenomenon between separated and shock-free scramjet modes based on steady quasi-one-dimensional combustor flow assumptions, and the second was between two different patterns of separated scramjet modes. Hysteresis mechanisms are elucidated from the viewpoint of combustion flow structures. The first hysteresis was attributed to flame stabilization mode transitions between the cavity shear-layer stabilized mode and the jet-wake stabilized mode, along with the transition hysteresis of a pre-combustion shock train's establishment and vanishment. The flame stabilization locations were greatly influenced by the flow separation states ahead of the fuel injectors, and the flow separations were in return determined by the flame distributions. The second hysteresis was attributed to transitions between weak-oscillation mode and intensive-oscillation mode with the transition hysteresis of shock reflection amount increase and decrease of the pre-combustion shock train structure, which were both in the jet-wake stabilized location. Flame in the low-speed region beside the separation bubbles ahead of the fuel injectors provided heat and hot radicals for downstream flame stabilization, and the pre-injector flame intensity greatly influenced the combustion oscillation states. (C) 2019 Elsevier Masson SAS. All rights reserved.
关键词	Hysteresis Dual-mode scramjet Supersonic combustion Mode transition Flame stabilization Combustion oscillation
DOI	10.1016/j.ast.2019.105420
收录类别	SCI ; EI
语种	英语
WOS记录号	WOS:000494053900049
关键词[WOS]	IGNITION TRANSIENTS ; PRESSURE ; ENGINE ; STABILIZATION ; OSCILLATIONS ; SIMULATIONS ; FLOW
WOS研究方向	Engineering
WOS类目	Engineering, Aerospace
资助项目	National Natural Science Foundation of China[11672309] ; National Natural Science Foundation of China[11472279]
项目资助者	National Natural Science Foundation of China
论文分区	一类
力学所作者排名	1
RpAuthor	Yue, Lianjie
引用统计	被引频次：24[WOS] [WOS记录] [WOS相关记录]
文献类型	期刊论文
条目标识符	http://dspace.imech.ac.cn/handle/311007/81380
专题	高温气体动力学国家重点实验室
作者单位	1.Chinese Acad Sci, Inst Mech, State Key Lab High Temp Gas Dynam, Beijing 100190, Peoples R China; 2.Univ Chinese Acad Sci, Sch Engn Sci, Beijing 100049, Peoples R China
推荐引用方式 GB/T 7714	Zhang X,Yue LJ,Huang TL,et al. Numerical investigation of mode transition and hysteresis in a cavity-based dual-mode scramjet combustor[J]. AEROSPACE SCIENCE AND TECHNOLOGY,2019,94:10.
APA	张旭,岳连捷,黄庭隆,张启帆,&张新宇.(2019).Numerical investigation of mode transition and hysteresis in a cavity-based dual-mode scramjet combustor.AEROSPACE SCIENCE AND TECHNOLOGY,94,10.
MLA	张旭,et al."Numerical investigation of mode transition and hysteresis in a cavity-based dual-mode scramjet combustor".AEROSPACE SCIENCE AND TECHNOLOGY 94(2019):10.

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