Numerical study of convective heat transfer of a supersonic combustor with varied inlet flow conditions
文献类型：期刊论文
| 作者 | Fan WH(范文慧)1,2; Zhong FQ(仲峰泉)1,2 ; Ma SG(马素刚)1; Zhang XY(张新宇)1,2
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| 刊名 | ACTA MECHANICA SINICA
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| 出版日期 | 2019-10-01 |
| 卷号 | 35期号:5页码:943-953 |
| 关键词 | Wall heat flux Numerical simulation Ethylene Supersonic combustor |
| ISSN号 | 0567-7718 |
| DOI | 10.1007/s10409-019-00882-x |
| 通讯作者 | Zhong, F. Q.(fzhong@imech.ac.cn) |
| 英文摘要 | Characteristics of convective heat transfer of a supersonic model combustor with variable inlet flow conditions were studied by numerical simulation in this paper. The three-dimensional flow and wall heat flux at different air inlet Mach numbers of 2.2, 2.8 and 3.2 were studied numerically with Reynolds-averaged Navier-Stokes equations with a shear-stress transport (SST) k-omega turbulence model and a three-step reaction model. Meanwhile, ethylene was chosen as the fuel, and the fixed fuel-to-air equivalence ratio is 0.8 in all cases in this paper. The results of the simulations indicate that wall heat flux distribution of the combustor is very non-uniform with several peaks of wall heat flux at varied locations. For the low inlet Mach number of 2.2, a shock train structure is formed in the isolator, and three peaks of wall heat flux are located respectively on the backward face of the cavity, on the side wall near the fuel injection and on the bottom wall near the injection holes, and a maximum wall heat flux reaches 5.4 MW/m(2). For the medium inlet Mach number of 2.8, there exists a much shorter shock structure with three peaks of wall heat flux similar to that of Mach number 2.2. However, as the inlet Mach number increased to 3.2, there is no shock structure upstream of fuel injections, and the combustor flow is in a supersonic mode with different locations and values of wall heat flux peaks. The statistical results of wall heat loading show that the change of total wall heat is not monotonic with the increase of inlet Mach number, and the maximum appears in the case of Mach number being 2.8. Meanwhile, for all the cases, the bottom wall takes up more than 50% of the total heat loading. |
| 分类号 | 二类 |
| WOS关键词 | SCRAMJET COMBUSTOR ; FLUX |
| 资助项目 | National Natural Science Foundation of China[11672307] ; Youth Innovation Promotion Association, Chinese Academy of Sciences |
| WOS研究方向 | Engineering ; Mechanics |
| 语种 | 英语 |
| WOS记录号 | WOS:000501851500001 |
| 资助机构 | National Natural Science Foundation of China ; Youth Innovation Promotion Association, Chinese Academy of Sciences |
| 其他责任者 | Zhong, F. Q. |
| 源URL | [http://dspace.imech.ac.cn/handle/311007/81230]  |
| 专题 | 力学研究所_高温气体动力学国家重点实验室 |
| 作者单位 | 1.Univ Chinese Acad Sci, Sch Engn Sci, Beijing 100049, Peoples R China 2.Chinese Acad Sci, Inst Mech, State Key Lab High Temp Gas Dynam, Beijing 100190, Peoples R China; |
| 推荐引用方式 GB/T 7714 | Fan WH,Zhong FQ,Ma SG,et al. Numerical study of convective heat transfer of a supersonic combustor with varied inlet flow conditions[J]. ACTA MECHANICA SINICA,2019,35(5):943-953. |
| APA | 范文慧,仲峰泉,马素刚,&张新宇.(2019).Numerical study of convective heat transfer of a supersonic combustor with varied inlet flow conditions.ACTA MECHANICA SINICA,35(5),943-953. |
| MLA | 范文慧,et al."Numerical study of convective heat transfer of a supersonic combustor with varied inlet flow conditions".ACTA MECHANICA SINICA 35.5(2019):943-953. |
入库方式： OAI收割
来源：力学研究所
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