中国科学院机构知识库网格
Chinese Academy of Sciences Institutional Repositories Grid
Numerical study on supersonic boundary-layer transition and wall skin friction reduction induced by fuel wall-jet combustion

文献类型:期刊论文

作者Xue R3,4; Zheng X4; Yue LJ(岳连捷)3; Zhang SK2; Weng C1
刊名ACTA ASTRONAUTICA
出版日期2020-09-01
卷号174页码:11-23
ISSN号0094-5765
关键词Compressible boundary layer combustion Skin-friction reduction Boundary layer transition Transition k-kl-w model Hydrogen combustion
DOI10.1016/j.actaastro.2020.04.031
英文摘要In this study, the effect of wall-jet combustion on boundary layer transition and skin friction reduction was numerically investigated. To effectively capture the characteristics of boundary layer flow, the transition k - kl - w model was employed as the turbulence model and laminar finite-rate model was chosen as the combustion model. This numerical method was firstly validated by two sets of experimental results in open domain. After that, the research on wall-jet combustion was conducted and the numerical results showed that when injecting hydrogen in different directions, both the hydrogen self-ignition location and the skin friction on the wall were not altered significantly. When the injection angle to the airflow direction was increased to 30 degrees, the intensity of combustion was insufficient and the skin-friction coefficient would be increased. Meanwhile, boundary layer transition occurred in a relatively smaller Reynolds number at this condition. The variation of the wall-jet height would have a greater impact on both boundary layer transition and the skin friction. More components can diffuse to the lower wall as the height of the wall-jet was enlarged, which can make the process of boundary layer transition be postponed and the skin friction be reduced as well. Furthermore, greater skin-friction reduction would be achieved downstream the self-ignition location when the wall was adiabatic, while the original Reynolds numbers for boundary layer transition is the smallest if the wall temperature is set to 600 K. Finally, in order to simulate the effect of the back pressure on the combustion flow field, another injector is added near the exit at the upper wall to produce air-throttling flow jet. The results showed that altering back pressure nearly has little influence on boundary layer transition and the skin friction decreases with more air-throttling flow rate.
分类号一类
WOS关键词HEAT-TRANSFER ; PREDICTION ; HYDROGEN
WOS研究方向Engineering
语种英语
WOS记录号WOS:000540350100002
资助机构National Natural Science Foundation of China[51706170] ; China Postdoctoral Science Foundation[2019TQ0246] ; China Postdoctoral Science Foundation[2019M663734] ; Foundation of State Key Laboratory of Coal Combustion[FSKLCCA2004] ; Natural Science Basic Research Program of Shaanxi[2020JQ-007] ; Foundation of State Key Laboratory of High Temperature Gas Dynamics ; Foundation of State Key Laboratory of Turbulence & Complex Systems ; Fundamental Research Funds for the Central Universities[xzy012019053] ; Fundamental Research Funds for the Central Universities[xjh012019033]
其他责任者Xue, Rui ; Zheng, Xing
源URL[http://dspace.imech.ac.cn/handle/311007/84724]  
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.Tongji Univ, Shanghai 200092, Peoples R China
2.Xian Modern Control Technol Res Inst, Xian 710065, Peoples R China;
3.Chinese Acad Sci, Inst Mech, State Key Lab High Temp Gas Dynam, Beijing 100190, Peoples R China;
4.Xi An Jiao Tong Univ, Sch Aerosp, State Key Lab Strength & Vibrat Mech Struct, Shaanxi Engn Lab Vibrat Control Aerosp Struct, Xian 710049, Peoples R China;
推荐引用方式
GB/T 7714
Xue R,Zheng X,Yue LJ,et al. Numerical study on supersonic boundary-layer transition and wall skin friction reduction induced by fuel wall-jet combustion[J]. ACTA ASTRONAUTICA,2020,174:11-23.
APA Xue R,Zheng X,岳连捷,Zhang SK,&Weng C.(2020).Numerical study on supersonic boundary-layer transition and wall skin friction reduction induced by fuel wall-jet combustion.ACTA ASTRONAUTICA,174,11-23.
MLA Xue R,et al."Numerical study on supersonic boundary-layer transition and wall skin friction reduction induced by fuel wall-jet combustion".ACTA ASTRONAUTICA 174(2020):11-23.

入库方式: OAI收割

来源:力学研究所

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