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Numerical study of combustion and convective heat transfer of a Mach 2.5 supersonic combustor
Wang X; Zhong FQ(仲峰泉); Gu HB(顾宏斌); Zhang XY(张新宇); Zhong, FQ (reprint author), 15 Beisihuanxi Rd, Beijing 100190, Peoples R China.
Source PublicationAPPLIED THERMAL ENGINEERING
2015-10-05
Volume89Pages:883-896
ISSN1359-4311
AbstractIn this paper, characteristics of combustion and convective heat transfer of a supersonic combustor at two fuel/air equivalence ratios of 0.9 and 0.46 were numerically studied. The numerical method of Favre averaged Navier-Stokes simulation with SST k-omega turbulence model and a multiple-step reaction mechanism of ethylene is introduced. The inlet Mach number of the combustor is 2.5 and inlet total temperature is 1650K, corresponding to Mach 6 flight conditions. Ethylene is injected at two locations upstream of a flame-holding cavity. The numerical method was validated by comparing the present results of wall pressures and heat fluxes to experiments and theoretical analysis. It is found that, due to injection of fuel at the bottom wall, fuel/air mixing and combustion occurs mainly in the vicinity of the bottom wall. High non-symmetry in distributions of the bottom and the top wall heat fluxes is observed. Peaks of wall heat flux at different locations and at varied fuel/air equivalence ratios are identified, which are caused respectively by effect of cavity and by shock structure formed upstream of the injection points. It is also found that heat flux peaks are strongly related to the reaction step of CO -> CO2, contributing to major heat releasing. (C) 2015 Elsevier Ltd. All rights reserved.
KeywordSupersonic Combustor Convective Heat Transfer Numerical Study Wall Heat Flux
DOI10.1016/j.applthermaleng.2015.06.071
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Indexed BySCI ; EI
Language英语
WOS IDWOS:000362862100084
WOS Research AreaThermodynamics ; Energy & Fuels ; Engineering ; Mechanics
WOS SubjectThermodynamics ; Energy & Fuels ; Engineering, Mechanical ; Mechanics
Funding OrganizationThis work is funded by Natural Science Foundation of China under Contract No. 11172309, 91441102.
DepartmentLHD高超声速推进技术
Classification一类
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Cited Times:7[WOS]   [WOS Record]     [Related Records in WOS]
Document Type期刊论文
Identifierhttp://dspace.imech.ac.cn/handle/311007/58395
Collection高温气体动力学国家重点实验室
Corresponding AuthorZhong, FQ (reprint author), 15 Beisihuanxi Rd, Beijing 100190, Peoples R China.
Recommended Citation
GB/T 7714
Wang X,Zhong FQ,Gu HB,et al. Numerical study of combustion and convective heat transfer of a Mach 2.5 supersonic combustor[J]. APPLIED THERMAL ENGINEERING,2015,89:883-896.
APA Wang X,Zhong FQ,Gu HB,Zhang XY,&Zhong, FQ .(2015).Numerical study of combustion and convective heat transfer of a Mach 2.5 supersonic combustor.APPLIED THERMAL ENGINEERING,89,883-896.
MLA Wang X,et al."Numerical study of combustion and convective heat transfer of a Mach 2.5 supersonic combustor".APPLIED THERMAL ENGINEERING 89(2015):883-896.
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