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Investigation of transient ignition process in a cavity based scramjet combustor using combined ethylene injectors

Liu, Xiao LU ; Cai, Zun; Tong, Yiheng LU and Zheng, Hongtao (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.

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author
organization
publishing date
type
Contribution to journal
publication status
published
subject
in
Acta Astronautica
volume
137
pages
7 pages
publisher
Elsevier
external identifiers
  • scopus:85017478272
  • wos:000405042000001
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
2018-04-08 04:56:26
@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},
  volume       = {137},
  year         = {2017},
}