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Numerical study of a fully confined supersonic slot impinging jet from bleed system
Huang TL(黄庭隆); Yue LJ(岳连捷); Chang XY(张新宇)
Source PublicationAEROSPACE SCIENCE AND TECHNOLOGY
2019-07-01
Volume90Pages:12-22
ISSN1270-9638
Abstract

A supersonic slot jet issuing from a bleed system and impinging into a plenum is numerically investigated to deepen our understanding of the flow field and heat transfer of a fully confined impinging jet. The air of the slot jet is forced to exhaust from a plenum in unidirection, resulting in a fully confined configuration. It is of significant practical interest because of its presence in the bleed systems of a scramjet or other related applications. Three primary factors are surveyed, i.e., impingement angle, impingement distance, and back pressure at the plenum exit. The results show that the supersonic slot jet spontaneously generates a plate shock standing on the impingement wall and a strong jet shock on the right side of the jet core. On the left side, the jet shear layer can directly impinge the wall because of the pressure self-adaption effect of a recirculation region. The jet shock and jet shear layer result in two peaks of Stanton number. As the impingement angle increases, the jet shock weakens gradually and moves toward the impingement region of the shear layer until the shock disappears. And thus a single heat peak occurs in place of the previous two peaks. When the downstream flow of the plenum is choked, a wall jet pattern is exhibited because of the formation of a large scale recirculation region. The walls suffer severe aerodynamic heating as the plenum back pressure increases. In particular, the impingement wall endures the maximum thermal load at a certain back pressure at which the jet reduces to the sound speed. The plenum should be controlled to keep the back pressure below this threshold so that the slot walls Stanton number won't increase further. And the plenum should be designed as high as possible to relieve its thermal load. (C) 2019 Elsevier Masson SAS. All rights reserved.

KeywordFully confined supersonic jet Inclined impingement Heat transfer Boundary layer bleed Numerical simulation
DOI10.1016/j.ast.2019.04.020
Indexed BySCI ; EI
Language英语
WOS IDWOS:000471357200002
WOS KeywordHEAT-TRANSFER ; HYPERSONIC INLETS ; IMPINGEMENT ; SHOCK ; SEPARATION ; MACH-6 ; PLATE
WOS Research AreaEngineering
WOS SubjectEngineering, Aerospace
Funding ProjectNational Natural Science Foundation of China[11672309] ; National Natural Science Foundation of China[11472279]
Funding OrganizationNational Natural Science Foundation of China
Classification一类
Ranking1
ContributorYue, Lianjie
Citation statistics
Document Type期刊论文
Identifierhttp://dspace.imech.ac.cn/handle/311007/79388
Collection高温气体动力学国家重点实验室
Recommended Citation
GB/T 7714
Huang TL,Yue LJ,Chang XY. Numerical study of a fully confined supersonic slot impinging jet from bleed system[J]. AEROSPACE SCIENCE AND TECHNOLOGY,2019,90:12-22.
APA Huang TL,Yue LJ,&Chang XY.(2019).Numerical study of a fully confined supersonic slot impinging jet from bleed system.AEROSPACE SCIENCE AND TECHNOLOGY,90,12-22.
MLA Huang TL,et al."Numerical study of a fully confined supersonic slot impinging jet from bleed system".AEROSPACE SCIENCE AND TECHNOLOGY 90(2019):12-22.
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