Subgrid models, reaction mechanisms, and combustion models in large-eddy simulation of supersonic combustion
(2021) In AIAA Journal 59(1). p.215-227- Abstract
Here, we report on large-eddy simulation (LES) of supersonic flow, mixing, self-ignition, and combustion in a model scramjet combustor. The combustor has been experimentally investigated at DLR, German Aerospace Center Lampoldshausen and consists of a one-sided divergent channel with a wedge-shaped flame-holder: at the base of which, hydrogen is injected. This combustor has been extensively studied by many research groups and constitutes a good validation case for model development and physics elucidation. The LES model used is based on an unstructured finite volume discretization of the filtered mass, momentum, species, and energy equations, as well as an explicit flow solver. Three subgrid flow models, three reaction mechanisms, and... (More)
Here, we report on large-eddy simulation (LES) of supersonic flow, mixing, self-ignition, and combustion in a model scramjet combustor. The combustor has been experimentally investigated at DLR, German Aerospace Center Lampoldshausen and consists of a one-sided divergent channel with a wedge-shaped flame-holder: at the base of which, hydrogen is injected. This combustor has been extensively studied by many research groups and constitutes a good validation case for model development and physics elucidation. The LES model used is based on an unstructured finite volume discretization of the filtered mass, momentum, species, and energy equations, as well as an explicit flow solver. Three subgrid flow models, three reaction mechanisms, and three LES combustion models are employed to examine the sensitivity to these modeling parameters. The LES predictions are compared with experimental data for velocity, temperature, wall pressure at different cross sections, as well as schlieren and OH chemiluminesence images, showing good agreement for both first-and second-order statistics, as well as the instantaneous flow structures. Furthermore, these LES results are used to illustrate and explain the intrinsic flow, mixing, and combustion features of this combustor. The intrinsic relationship between the different modeling parameters is also discussed.
(Less)
- author
- Fureby, C. LU
- organization
- publishing date
- 2021
- type
- Contribution to journal
- publication status
- published
- subject
- in
- AIAA Journal
- volume
- 59
- issue
- 1
- pages
- 13 pages
- publisher
- American Institute of Aeronautics and Astronautics
- external identifiers
-
- scopus:85099060832
- ISSN
- 0001-1452
- DOI
- 10.2514/1.J059597
- language
- English
- LU publication?
- yes
- id
- 639461dc-fe62-494d-ac92-48c4fca414c4
- date added to LUP
- 2021-01-19 14:26:28
- date last changed
- 2022-04-26 23:45:36
@article{639461dc-fe62-494d-ac92-48c4fca414c4,
abstract = {{<p>Here, we report on large-eddy simulation (LES) of supersonic flow, mixing, self-ignition, and combustion in a model scramjet combustor. The combustor has been experimentally investigated at DLR, German Aerospace Center Lampoldshausen and consists of a one-sided divergent channel with a wedge-shaped flame-holder: at the base of which, hydrogen is injected. This combustor has been extensively studied by many research groups and constitutes a good validation case for model development and physics elucidation. The LES model used is based on an unstructured finite volume discretization of the filtered mass, momentum, species, and energy equations, as well as an explicit flow solver. Three subgrid flow models, three reaction mechanisms, and three LES combustion models are employed to examine the sensitivity to these modeling parameters. The LES predictions are compared with experimental data for velocity, temperature, wall pressure at different cross sections, as well as schlieren and OH chemiluminesence images, showing good agreement for both first-and second-order statistics, as well as the instantaneous flow structures. Furthermore, these LES results are used to illustrate and explain the intrinsic flow, mixing, and combustion features of this combustor. The intrinsic relationship between the different modeling parameters is also discussed.</p>}},
author = {{Fureby, C.}},
issn = {{0001-1452}},
language = {{eng}},
number = {{1}},
pages = {{215--227}},
publisher = {{American Institute of Aeronautics and Astronautics}},
series = {{AIAA Journal}},
title = {{Subgrid models, reaction mechanisms, and combustion models in large-eddy simulation of supersonic combustion}},
url = {{http://dx.doi.org/10.2514/1.J059597}},
doi = {{10.2514/1.J059597}},
volume = {{59}},
year = {{2021}},
}