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LES of supersonic combustion in a scramjet engine model

Berglund, Magnus LU and Fureby, C (2007) In Proceedings of the Combustion Institute 31. p.2497-2504
Abstract
In this study, Large Eddy Simulation (LES) has been used to examine supersonic flow and combustion in a model scramjet combustor. The LES model is based on an unstructured finite volume discretization, using total variational diminishing flux reconstruction, of the filtered continuity, momentum, enthalpy, and passive/reactive scalar equations, used to describe the combustion process. The configuration used is similar to the laboratory scrarmjet at the Institute for Chemical Propulsion of the German Aerospace Center (DLR) and consists of a one-sided divergent channel with a wedge-shaped flameholder at the base of which hydrogen is injected. Here, we investigate supersonic flow with hydrogen injection and supersonic flow with hydrogen... (More)
In this study, Large Eddy Simulation (LES) has been used to examine supersonic flow and combustion in a model scramjet combustor. The LES model is based on an unstructured finite volume discretization, using total variational diminishing flux reconstruction, of the filtered continuity, momentum, enthalpy, and passive/reactive scalar equations, used to describe the combustion process. The configuration used is similar to the laboratory scrarmjet at the Institute for Chemical Propulsion of the German Aerospace Center (DLR) and consists of a one-sided divergent channel with a wedge-shaped flameholder at the base of which hydrogen is injected. Here, we investigate supersonic flow with hydrogen injection and supersonic flow with hydrogen injection and combustion. For the purpose of validation, the LES results are compared with experimental data for velocity and temperature at different cross-sections. In addition, qualitative comparisons are also made between predicted and measured shadowgraph images. The LES computations are capable of predicting both the non-reacting and reacting flowfields reasonably well-in particular we notice that the LES model identifies and differentiates between peculiarities of the flowfields found in the experiments. (c) 2006 The Combustion Institute. Published by Elsevier Inc. All rights reserved. (Less)
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author
organization
publishing date
type
Contribution to journal
publication status
published
subject
keywords
scramjet, supersonic combustion, Large Eddy Simulation, flamelet model
in
Proceedings of the Combustion Institute
volume
31
pages
2497 - 2504
publisher
Elsevier
external identifiers
  • wos:000252858200093
  • scopus:34548784285
ISSN
1540-7489
DOI
10.1016/j.proci.2006.07.074
language
English
LU publication?
yes
id
5a2d0992-bf28-4630-89ae-6f86c01a17c6 (old id 1407668)
date added to LUP
2009-05-29 14:08:07
date last changed
2017-11-05 03:29:48
@article{5a2d0992-bf28-4630-89ae-6f86c01a17c6,
  abstract     = {In this study, Large Eddy Simulation (LES) has been used to examine supersonic flow and combustion in a model scramjet combustor. The LES model is based on an unstructured finite volume discretization, using total variational diminishing flux reconstruction, of the filtered continuity, momentum, enthalpy, and passive/reactive scalar equations, used to describe the combustion process. The configuration used is similar to the laboratory scrarmjet at the Institute for Chemical Propulsion of the German Aerospace Center (DLR) and consists of a one-sided divergent channel with a wedge-shaped flameholder at the base of which hydrogen is injected. Here, we investigate supersonic flow with hydrogen injection and supersonic flow with hydrogen injection and combustion. For the purpose of validation, the LES results are compared with experimental data for velocity and temperature at different cross-sections. In addition, qualitative comparisons are also made between predicted and measured shadowgraph images. The LES computations are capable of predicting both the non-reacting and reacting flowfields reasonably well-in particular we notice that the LES model identifies and differentiates between peculiarities of the flowfields found in the experiments. (c) 2006 The Combustion Institute. Published by Elsevier Inc. All rights reserved.},
  author       = {Berglund, Magnus and Fureby, C},
  issn         = {1540-7489},
  keyword      = {scramjet,supersonic combustion,Large Eddy Simulation,flamelet model},
  language     = {eng},
  pages        = {2497--2504},
  publisher    = {Elsevier},
  series       = {Proceedings of the Combustion Institute},
  title        = {LES of supersonic combustion in a scramjet engine model},
  url          = {http://dx.doi.org/10.1016/j.proci.2006.07.074},
  volume       = {31},
  year         = {2007},
}