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Numerical studies on supersonic spray combustion in high-temperature shear flows in a scramjet combustor

Zhaoxin Ren Orcid Logo, Bing WANG, Longxi ZHENG, Dan ZHAO

Chinese Journal of Aeronautics, Volume: 31, Issue: 9, Pages: 1870 - 1879

Swansea University Author: Zhaoxin Ren Orcid Logo

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DOI (Published version): 10.1016/j.cja.2018.06.020

Abstract

Numerical simulation is applied to detail the combustion characteristics of n-decane sprays in highly compressible vortices formed in a supersonic mixing layer. The multi-phase reacting flow is modeled, in which the shear flow is solved Eulerianly by means of direct numerical simulation, and the mot...

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Published in: Chinese Journal of Aeronautics
ISSN: 1000-9361
Published: Elsevier BV 2018
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URI: https://cronfa.swan.ac.uk/Record/cronfa59354
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spelling 2022-03-03T13:41:25.3692964 v2 59354 2022-02-11 Numerical studies on supersonic spray combustion in high-temperature shear flows in a scramjet combustor 62a1a0da0fa78e05c3deafcdee5551ce 0000-0002-6305-9515 Zhaoxin Ren Zhaoxin Ren true false 2022-02-11 AERO Numerical simulation is applied to detail the combustion characteristics of n-decane sprays in highly compressible vortices formed in a supersonic mixing layer. The multi-phase reacting flow is modeled, in which the shear flow is solved Eulerianly by means of direct numerical simulation, and the motions of individual sub-grid point-mass fuel droplets are tracked Lagrangianly. Spray combustion behaviors are studied under different ambient pressures. Results indicate that ignition kernels are formed at high-strain vortex braids, where the scalar dissipation rates are high. The flame kernels are then strongly strained, associated with the rotation of the shearing vortex, and propagate to envelop the local vortex. It is observed that the flammable mixtures entrained in the vortex are burned from the edge to the core of the vortex until the reactants are completely consumed. As the ambient pressure increases, the high-temperature region expands so that the behaviors of spray flames are strongly changed. An overall analysis of the combustion field indicates that the time-averaged temperature increases, and the fluctuating pressure decreases, resulting in a more stable spray combustion under higher pressures, primarily due to the acceleration of the chemical reaction. Journal Article Chinese Journal of Aeronautics 31 9 1870 1879 Elsevier BV 1000-9361 Combustion; Flame kernel; Mixing layer; Numerical simulation; Shearing vortex; Spray flame; Supersonic flow 21 9 2018 2018-09-21 10.1016/j.cja.2018.06.020 COLLEGE NANME Aerospace Engineering COLLEGE CODE AERO Swansea University The second author would like to thank the partial finical supports from the National Natural Science Foundation of China (No. 51676111), the Joint Fund of the National Natural Science Foundation of China and the China Academy of Engineering Physics (No. U1730104), and the Tsinghua University Initiative Scientific Research Program, China (No. 2014Z05091). 2022-03-03T13:41:25.3692964 2022-02-11T01:07:36.2293252 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 Longxi ZHENG 3 Dan ZHAO 4 59354__22502__a5d065317c864c4497fcaa526ca70815.pdf 59354.pdf 2022-03-03T13:39:43.8919713 Output 2154017 application/pdf Version of Record true Copyright: 2018 Chinese Society of Aeronautics and Astronautics. This is an open access article under the CC BY-NC-ND license true eng http://creativecommons.org/licenses/by-nc-nd/4.0/
title Numerical studies on supersonic spray combustion in high-temperature shear flows in a scramjet combustor
spellingShingle Numerical studies on supersonic spray combustion in high-temperature shear flows in a scramjet combustor
Zhaoxin Ren
title_short Numerical studies on supersonic spray combustion in high-temperature shear flows in a scramjet combustor
title_full Numerical studies on supersonic spray combustion in high-temperature shear flows in a scramjet combustor
title_fullStr Numerical studies on supersonic spray combustion in high-temperature shear flows in a scramjet combustor
title_full_unstemmed Numerical studies on supersonic spray combustion in high-temperature shear flows in a scramjet combustor
title_sort Numerical studies on supersonic spray combustion in high-temperature shear flows in a scramjet combustor
author_id_str_mv 62a1a0da0fa78e05c3deafcdee5551ce
author_id_fullname_str_mv 62a1a0da0fa78e05c3deafcdee5551ce_***_Zhaoxin Ren
author Zhaoxin Ren
author2 Zhaoxin Ren
Bing WANG
Longxi ZHENG
Dan ZHAO
format Journal article
container_title Chinese Journal of Aeronautics
container_volume 31
container_issue 9
container_start_page 1870
publishDate 2018
institution Swansea University
issn 1000-9361
doi_str_mv 10.1016/j.cja.2018.06.020
publisher Elsevier BV
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 Numerical simulation is applied to detail the combustion characteristics of n-decane sprays in highly compressible vortices formed in a supersonic mixing layer. The multi-phase reacting flow is modeled, in which the shear flow is solved Eulerianly by means of direct numerical simulation, and the motions of individual sub-grid point-mass fuel droplets are tracked Lagrangianly. Spray combustion behaviors are studied under different ambient pressures. Results indicate that ignition kernels are formed at high-strain vortex braids, where the scalar dissipation rates are high. The flame kernels are then strongly strained, associated with the rotation of the shearing vortex, and propagate to envelop the local vortex. It is observed that the flammable mixtures entrained in the vortex are burned from the edge to the core of the vortex until the reactants are completely consumed. As the ambient pressure increases, the high-temperature region expands so that the behaviors of spray flames are strongly changed. An overall analysis of the combustion field indicates that the time-averaged temperature increases, and the fluctuating pressure decreases, resulting in a more stable spray combustion under higher pressures, primarily due to the acceleration of the chemical reaction.
published_date 2018-09-21T04:16:36Z
_version_ 1763754111132499968
score 11.013731

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