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Response of dispersed droplets to shock waves in supersonic mixing layers

Zhaoxin Ren Orcid Logo, Bing Wang

Advances in Mechanical Engineering, Volume: 7, Issue: 6, Start page: 168781401558849

Swansea University Author: Zhaoxin Ren Orcid Logo

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DOI (Published version): 10.1177/1687814015588492

Abstract

The response of dispersed droplets to oblique shock waves in the supersonic mixing layer was investigated using the large eddy simulation coupled with the particle Lagrangian tracking model. The generated disturbances based on the most-unstable wave model were imposed to excite the development of su...

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Published in: Advances in Mechanical Engineering
ISSN: 1687-8140 1687-8140
Published: SAGE Publications 2015
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URI: https://cronfa.swan.ac.uk/Record/cronfa59360
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spelling 2022-02-23T15:27:35.7234412 v2 59360 2022-02-11 Response of dispersed droplets to shock waves in supersonic mixing layers 62a1a0da0fa78e05c3deafcdee5551ce 0000-0002-6305-9515 Zhaoxin Ren Zhaoxin Ren true false 2022-02-11 AERO The response of dispersed droplets to oblique shock waves in the supersonic mixing layer was investigated using the large eddy simulation coupled with the particle Lagrangian tracking model. The generated disturbances based on the most-unstable wave model were imposed to excite the development of supersonic shear layer. The oblique shock wave was numerically introduced in the flow field. Small- and medium-sized droplets remained their preferential distribution in the vortices after crossing the shock wave, while large-sized droplet became more dispersed. The influence of shock waves on the momentum and heat transfers from surrounding gas to droplets was analyzed by tracking droplets’ motion paths. Small-sized droplets responded easily to the shock wave. Compared with the aerodynamic response, the thermal response of droplets was slower, especially under the impaction of the shock wave. The present research conclusions are conductive to analyze the mixing of air and fuel droplets and of important academic value for further understanding the two-phase dynamics in combustors of scramjet. Journal Article Advances in Mechanical Engineering 7 6 168781401558849 SAGE Publications 1687-8140 1687-8140 Supersonic two-phase flow, oblique shock wave, response behavior, large eddy simulation, Lagrangian trajectory model 1 6 2015 2015-06-01 10.1177/1687814015588492 COLLEGE NANME Aerospace Engineering COLLEGE CODE AERO Swansea University This work was partially funded by the Importation and Development of High-Caliber Talents Project of Beijing Municipal Institutions (No.YETP0113). 2022-02-23T15:27:35.7234412 2022-02-11T01:09:02.0824499 Faculty of Science and Engineering School of Aerospace, Civil, Electrical, General and Mechanical Engineering - Aerospace Engineering Zhaoxin Ren 0000-0002-6305-9515 1 Bing Wang 2 59360__22442__560ebb82db154e61a3176b57eed089dc.pdf 59360.pdf 2022-02-23T15:26:34.0385259 Output 2694941 application/pdf Version of Record true This article is distributed under the terms of the Creative Commons Attribution 3.0 License true eng http://www.creativecommons.org/licenses/by/3.0/
title Response of dispersed droplets to shock waves in supersonic mixing layers
spellingShingle Response of dispersed droplets to shock waves in supersonic mixing layers
Zhaoxin Ren
title_short Response of dispersed droplets to shock waves in supersonic mixing layers
title_full Response of dispersed droplets to shock waves in supersonic mixing layers
title_fullStr Response of dispersed droplets to shock waves in supersonic mixing layers
title_full_unstemmed Response of dispersed droplets to shock waves in supersonic mixing layers
title_sort Response of dispersed droplets to shock waves in supersonic mixing layers
author_id_str_mv 62a1a0da0fa78e05c3deafcdee5551ce
author_id_fullname_str_mv 62a1a0da0fa78e05c3deafcdee5551ce_***_Zhaoxin Ren
author Zhaoxin Ren
author2 Zhaoxin Ren
Bing Wang
format Journal article
container_title Advances in Mechanical Engineering
container_volume 7
container_issue 6
container_start_page 168781401558849
publishDate 2015
institution Swansea University
issn 1687-8140
1687-8140
doi_str_mv 10.1177/1687814015588492
publisher SAGE Publications
college_str Faculty of Science and Engineering
hierarchytype
hierarchy_top_id facultyofscienceandengineering
hierarchy_top_title Faculty of Science and Engineering
hierarchy_parent_id facultyofscienceandengineering
hierarchy_parent_title Faculty of Science and Engineering
department_str School of Aerospace, Civil, Electrical, General and Mechanical Engineering - Aerospace Engineering{{{_:::_}}}Faculty of Science and Engineering{{{_:::_}}}School of Aerospace, Civil, Electrical, General and Mechanical Engineering - Aerospace Engineering
document_store_str 1
active_str 0
description The response of dispersed droplets to oblique shock waves in the supersonic mixing layer was investigated using the large eddy simulation coupled with the particle Lagrangian tracking model. The generated disturbances based on the most-unstable wave model were imposed to excite the development of supersonic shear layer. The oblique shock wave was numerically introduced in the flow field. Small- and medium-sized droplets remained their preferential distribution in the vortices after crossing the shock wave, while large-sized droplet became more dispersed. The influence of shock waves on the momentum and heat transfers from surrounding gas to droplets was analyzed by tracking droplets’ motion paths. Small-sized droplets responded easily to the shock wave. Compared with the aerodynamic response, the thermal response of droplets was slower, especially under the impaction of the shock wave. The present research conclusions are conductive to analyze the mixing of air and fuel droplets and of important academic value for further understanding the two-phase dynamics in combustors of scramjet.
published_date 2015-06-01T04:16:36Z
_version_ 1763754111746965504
score 11.013731

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