Journal article 498 views 83 downloads
Response of dispersed droplets to shock waves in supersonic mixing layers
Advances in Mechanical Engineering, Volume: 7, Issue: 6, Start page: 168781401558849
Swansea University Author:
Zhaoxin Ren
-
PDF | Version of Record
This article is distributed under the terms of the Creative Commons Attribution 3.0 License
Download (2.57MB)
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...
Published in: | Advances in Mechanical Engineering |
---|---|
ISSN: | 1687-8140 1687-8140 |
Published: |
SAGE Publications
2015
|
Online Access: |
Check full text
|
URI: | https://cronfa.swan.ac.uk/Record/cronfa59360 |
Tags: |
Add Tag
No Tags, Be the first to tag this record!
|
first_indexed |
2022-02-15T02:53:29Z |
---|---|
last_indexed |
2022-02-24T04:28:29Z |
id |
cronfa59360 |
recordtype |
SURis |
fullrecord |
<?xml version="1.0"?><rfc1807><datestamp>2022-02-23T15:27:35.7234412</datestamp><bib-version>v2</bib-version><id>59360</id><entry>2022-02-11</entry><title>Response of dispersed droplets to shock waves in supersonic mixing layers</title><swanseaauthors><author><sid>62a1a0da0fa78e05c3deafcdee5551ce</sid><ORCID>0000-0002-6305-9515</ORCID><firstname>Zhaoxin</firstname><surname>Ren</surname><name>Zhaoxin Ren</name><active>true</active><ethesisStudent>false</ethesisStudent></author></swanseaauthors><date>2022-02-11</date><deptcode>AERO</deptcode><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 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.</abstract><type>Journal Article</type><journal>Advances in Mechanical Engineering</journal><volume>7</volume><journalNumber>6</journalNumber><paginationStart>168781401558849</paginationStart><paginationEnd/><publisher>SAGE Publications</publisher><placeOfPublication/><isbnPrint/><isbnElectronic/><issnPrint>1687-8140</issnPrint><issnElectronic>1687-8140</issnElectronic><keywords>Supersonic two-phase flow, oblique shock wave, response behavior, large eddy simulation, Lagrangian trajectory model</keywords><publishedDay>1</publishedDay><publishedMonth>6</publishedMonth><publishedYear>2015</publishedYear><publishedDate>2015-06-01</publishedDate><doi>10.1177/1687814015588492</doi><url/><notes/><college>COLLEGE NANME</college><department>Aerospace Engineering</department><CollegeCode>COLLEGE CODE</CollegeCode><DepartmentCode>AERO</DepartmentCode><institution>Swansea University</institution><apcterm/><funders>This work was partially funded by the Importation and Development of High-Caliber Talents Project of Beijing Municipal Institutions (No.YETP0113).</funders><lastEdited>2022-02-23T15:27:35.7234412</lastEdited><Created>2022-02-11T01:09:02.0824499</Created><path><level id="1">Faculty of Science and Engineering</level><level id="2">School of Aerospace, Civil, Electrical, General and Mechanical Engineering - Aerospace Engineering</level></path><authors><author><firstname>Zhaoxin</firstname><surname>Ren</surname><orcid>0000-0002-6305-9515</orcid><order>1</order></author><author><firstname>Bing</firstname><surname>Wang</surname><order>2</order></author></authors><documents><document><filename>59360__22442__560ebb82db154e61a3176b57eed089dc.pdf</filename><originalFilename>59360.pdf</originalFilename><uploaded>2022-02-23T15:26:34.0385259</uploaded><type>Output</type><contentLength>2694941</contentLength><contentType>application/pdf</contentType><version>Version of Record</version><cronfaStatus>true</cronfaStatus><documentNotes>This article is distributed under the terms of the Creative Commons Attribution 3.0 License</documentNotes><copyrightCorrect>true</copyrightCorrect><language>eng</language><licence>http://www.creativecommons.org/licenses/by/3.0/</licence></document></documents><OutputDurs/></rfc1807> |
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 |
11.021648 |