Numerical study of combustion and convective heat transfer of a Mach 2.5 supersonic combustor
文献类型：期刊论文
| 作者 | Wang X; Zhong FQ(仲峰泉) ; Gu HB(顾宏斌); Zhang XY(张新宇)
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| 刊名 | APPLIED THERMAL ENGINEERING
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| 出版日期 | 2015-10-05 |
| 卷号 | 89页码:883-896 |
| 通讯作者邮箱 | fzhong@imech.ac.cn |
| 关键词 | Supersonic combustor Convective heat transfer Numerical study Wall heat flux |
| ISSN号 | 1359-4311 |
| 产权排序 | [Wang, Xi; Zhong, Fengquan; Gu, Hongbin; Zhang, Xinyu] Chinese Acad Sci, Inst Mech, State Key Lab High Temp Gas Dynam, Beijing 100864, Peoples R China |
| 通讯作者 | Zhong, FQ (reprint author), 15 Beisihuanxi Rd, Beijing 100190, Peoples R China. |
| 中文摘要 | In 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. |
| 分类号 | 一类 |
| 类目[WOS] | Thermodynamics ; Energy & Fuels ; Engineering, Mechanical ; Mechanics |
| 研究领域[WOS] | Thermodynamics ; Energy & Fuels ; Engineering ; Mechanics |
| 收录类别 | SCI ; EI |
| 原文出处 | http://dx.doi.org/10.1016/j.applthermaleng.2015.06.071 |
| 语种 | 英语 |
| WOS记录号 | WOS:000362862100084 |
| 源URL | [http://dspace.imech.ac.cn/handle/311007/58395]  |
| 专题 | 力学研究所_高温气体动力学国家重点实验室 |
| 推荐引用方式 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.(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. |
入库方式： OAI收割
来源：力学研究所
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