Large Eddy Simulation of the flame propagation process in an ethylene fueled scramjet combustor in a supersonic flow
(2017) 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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- author
- Cai, Zun ; Wang, Zhenguo ; Sun, Mingbo and Bai, Xue Song LU
- organization
- publishing date
- 2017
- type
- Chapter in Book/Report/Conference proceeding
- publication status
- published
- subject
- host publication
- 21st AIAA International Space Planes and Hypersonics Technologies Conference, Hypersonics 2017
- publisher
- American Institute of Aeronautics and Astronautics
- conference name
- 21st AIAA International Space Planes and Hypersonics Technologies Conference, Hypersonics 2017
- conference location
- Xiamen, China
- conference dates
- 2017-03-06 - 2017-03-09
- 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
- 2025-04-04 14:02:15
@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}},
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}},
doi = {{10.2514/6.2017-2148}},
year = {{2017}},
}