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Large Eddy Simulation of the flame propagation process in an ethylene fueled scramjet combustor in a supersonic flow

Cai, Zun; Wang, Zhenguo; Sun, Mingbo and Bai, Xue Song LU (2017) 21st AIAA International Space Planes and Hypersonics Technologies Conference, Hypersonics 2017 In 21st AIAA International Space Planes and Hypersonics Technologies Conference, Hypersonics 2017
Abstract

Large Eddy Simulation (LES) was employed to investigate the flow field characteristics in an ethylene fueled scramjet combustor with a rearwall-expansion cavity in both non-reaction and reacting flows. The numerical solver was first validated against experiments and the numerical results were shown in reasonably good agreement with the available experimental data. Characteristics of the flow field under different combined fuel injection schemes were then studied. It was found thatfor the flame stabilizationprocess, applying the cavity direct injection on the cavity leading edge could improve the combustion process outside the cavity effectively witha fast combustion rate achieved in the region downstream the cavity. In contrast,... (More)

Large Eddy Simulation (LES) was employed to investigate the flow field characteristics in an ethylene fueled scramjet combustor with a rearwall-expansion cavity in both non-reaction and reacting flows. The numerical solver was first validated against experiments and the numerical results were shown in reasonably good agreement with the available experimental data. Characteristics of the flow field under different combined fuel injection schemes were then studied. It was found thatfor the flame stabilizationprocess, applying the cavity direct injection on the cavity leading edge could improve the combustion process outside the cavity effectively witha fast combustion rate achieved in the region downstream the cavity. In contrast, applying the cavity direct injection on the cavity rear wall is more suitable for improving the combustion process inside the cavity and a more evenly distributed flame would be stabilized in the entire combustor. However, the combustion rate downstream the cavity will be slower. For the rearwall-expansion cavity, both the non-reaction and reacting processes could be improved by applying the combined fuel injection scheme.

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publication status
published
subject
in
21st AIAA International Space Planes and Hypersonics Technologies Conference, Hypersonics 2017
publisher
American Institute of Aeronautics and Astronautics Inc. (AIAA)
conference name
21st AIAA International Space Planes and Hypersonics Technologies Conference, Hypersonics 2017
external identifiers
  • scopus:85017562220
ISBN
9781624104633
DOI
10.2514/6.2017-2148
language
English
LU publication?
yes
id
b121e791-0dd5-497e-8d98-10f73013afc1
date added to LUP
2017-05-08 16:15:16
date last changed
2017-05-08 16:15:16
@inproceedings{b121e791-0dd5-497e-8d98-10f73013afc1,
  abstract     = {<p>Large Eddy Simulation (LES) was employed to investigate the flow field characteristics in an ethylene fueled scramjet combustor with a rearwall-expansion cavity in both non-reaction and reacting flows. The numerical solver was first validated against experiments and the numerical results were shown in reasonably good agreement with the available experimental data. Characteristics of the flow field under different combined fuel injection schemes were then studied. It was found thatfor the flame stabilizationprocess, applying the cavity direct injection on the cavity leading edge could improve the combustion process outside the cavity effectively witha fast combustion rate achieved in the region downstream the cavity. In contrast, applying the cavity direct injection on the cavity rear wall is more suitable for improving the combustion process inside the cavity and a more evenly distributed flame would be stabilized in the entire combustor. However, the combustion rate downstream the cavity will be slower. For the rearwall-expansion cavity, both the non-reaction and reacting processes could be improved by applying the combined fuel injection scheme.</p>},
  author       = {Cai, Zun and Wang, Zhenguo and Sun, Mingbo and Bai, Xue Song},
  booktitle    = {21st AIAA International Space Planes and Hypersonics Technologies Conference, Hypersonics 2017},
  isbn         = {9781624104633},
  language     = {eng},
  publisher    = {American Institute of Aeronautics and Astronautics Inc. (AIAA)},
  title        = {Large Eddy Simulation of the flame propagation process in an ethylene fueled scramjet combustor in a supersonic flow},
  url          = {http://dx.doi.org/10.2514/6.2017-2148},
  year         = {2017},
}