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Numerical study of convective heat transfer of a supersonic combustor with varied inlet flow conditions
Fan WH(范文慧)1,2; Zhong FQ(仲峰泉)1,2; Ma SG(马素刚)2; Zhang XY(张新宇)1,2
Corresponding AuthorZhong, F. Q.(fzhong@imech.ac.cn)
Source PublicationACTA MECHANICA SINICA
2019-10-01
Volume35Issue:5Pages:943-953
ISSN0567-7718
AbstractCharacteristics 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.
KeywordWall heat flux Numerical simulation Ethylene Supersonic combustor
DOI10.1007/s10409-019-00882-x
Indexed BySCI ; EI ; CSCD
Language英语
WOS IDWOS:000501851500001
WOS KeywordSCRAMJET COMBUSTOR ; FLUX
WOS Research AreaEngineering ; Mechanics
WOS SubjectEngineering, Mechanical ; Mechanics
Funding ProjectNational Natural Science Foundation of China[11672307] ; Youth Innovation Promotion Association, Chinese Academy of Sciences
Funding OrganizationNational Natural Science Foundation of China ; Youth Innovation Promotion Association, Chinese Academy of Sciences
Classification二类
Ranking1
ContributorZhong, F. Q.
Citation statistics
Document Type期刊论文
Identifierhttp://dspace.imech.ac.cn/handle/311007/81231
Collection高温气体动力学国家重点实验室
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
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.
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