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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
Corresponding AuthorYue, Lianjie(
AbstractThe 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.
KeywordHysteresis Dual-mode scramjet Supersonic combustion Mode transition Flame stabilization Combustion oscillation
Indexed BySCI ; EI
WOS IDWOS:000494053900049
WOS Research AreaEngineering
WOS SubjectEngineering, Aerospace
Funding ProjectNational Natural Science Foundation of China[11672309] ; National Natural Science Foundation of China[11472279]
Funding OrganizationNational Natural Science Foundation of China
ContributorYue, Lianjie
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Cited Times:6[WOS]   [WOS Record]     [Related Records in WOS]
Document Type期刊论文
Affiliation1.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
Recommended Citation
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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