Investigation of transient ignition process in a cavity based scramjet combustor using combined ethylene injectors
(2017) In Acta Astronautica 137. p.1-7- Abstract
Large Eddy Simulation (LES) and experiment were employed to investigate the transient ignition and flame propagation process in a rearwall-expansion cavity scramjet combustor using combined fuel injection schemes. The compressible supersonic solver and three ethylene combustion mechanisms were first validated against experimental data and results show in reasonably good agreement. Fuel injection scheme combining transverse and direct injectors in the cavity provides a benefit mixture distribution and could achieve a successful ignition. Four stages are illustrated in detail from both experiment and LES. After forced ignition in the cavity, initial flame kernel propagates upstream towards the cavity front edge and ignites the mixture,... (More)
Large Eddy Simulation (LES) and experiment were employed to investigate the transient ignition and flame propagation process in a rearwall-expansion cavity scramjet combustor using combined fuel injection schemes. The compressible supersonic solver and three ethylene combustion mechanisms were first validated against experimental data and results show in reasonably good agreement. Fuel injection scheme combining transverse and direct injectors in the cavity provides a benefit mixture distribution and could achieve a successful ignition. Four stages are illustrated in detail from both experiment and LES. After forced ignition in the cavity, initial flame kernel propagates upstream towards the cavity front edge and ignites the mixture, which acts as a continuous pilot flame, and then propagates downstream along the cavity shear layer rapidly to the combustor exit. Cavity shear layer flame stabilization mode can be concluded from the heat release rate and local high temperature distribution during the combustion process.
(Less)
- author
- Liu, Xiao LU ; Cai, Zun ; Tong, Yiheng LU and Zheng, Hongtao
- organization
- publishing date
- 2017-08-01
- type
- Contribution to journal
- publication status
- published
- subject
- in
- Acta Astronautica
- volume
- 137
- pages
- 7 pages
- publisher
- Elsevier
- external identifiers
-
- wos:000405042000001
- scopus:85017478272
- ISSN
- 0094-5765
- DOI
- 10.1016/j.actaastro.2017.04.007
- language
- English
- LU publication?
- yes
- id
- 452039d5-778b-424a-8b68-0fddb18ae9fb
- date added to LUP
- 2017-05-08 10:01:57
- date last changed
- 2024-06-09 15:55:06
@article{452039d5-778b-424a-8b68-0fddb18ae9fb,
abstract = {{<p>Large Eddy Simulation (LES) and experiment were employed to investigate the transient ignition and flame propagation process in a rearwall-expansion cavity scramjet combustor using combined fuel injection schemes. The compressible supersonic solver and three ethylene combustion mechanisms were first validated against experimental data and results show in reasonably good agreement. Fuel injection scheme combining transverse and direct injectors in the cavity provides a benefit mixture distribution and could achieve a successful ignition. Four stages are illustrated in detail from both experiment and LES. After forced ignition in the cavity, initial flame kernel propagates upstream towards the cavity front edge and ignites the mixture, which acts as a continuous pilot flame, and then propagates downstream along the cavity shear layer rapidly to the combustor exit. Cavity shear layer flame stabilization mode can be concluded from the heat release rate and local high temperature distribution during the combustion process.</p>}},
author = {{Liu, Xiao and Cai, Zun and Tong, Yiheng and Zheng, Hongtao}},
issn = {{0094-5765}},
language = {{eng}},
month = {{08}},
pages = {{1--7}},
publisher = {{Elsevier}},
series = {{Acta Astronautica}},
title = {{Investigation of transient ignition process in a cavity based scramjet combustor using combined ethylene injectors}},
url = {{http://dx.doi.org/10.1016/j.actaastro.2017.04.007}},
doi = {{10.1016/j.actaastro.2017.04.007}},
volume = {{137}},
year = {{2017}},
}