A practical model for the high-altitude relight of a gas turbine combustor
A practical model for the high-altitude relight of a gas turbine combustor
A model that simulates the possible flame trajectories following spark ignition in a generic recirculating flame has been applied to a realistic aero-engine combustor. The model has been previously validated for gaseous and simple spray flames. It uses a CFD solution of the un-ignited flow and estimates the volume of the combustor that could be ignited given a particular flow field, spray distribution, and spark location, shape and size, and also provides a measure of the variability between independent sparking events. From this information, the ease of igniting the combustor can be assessed, and hence the combustor and injector geometry and spark placement decisions can be informed at a very early stage of the design process. Results for igniting a Rolls-Royce test combustor run with kerosene at high-altitude relight conditions for which experimental data are available and for which a RANS CFD solution has been developed, demonstrate the usefulness of the model’s output. The results are consistent with experiment and also reveal that the spark characteristics and location used in the experiments, developed over a number of years by trial-and-error methods, are indeed close to optimum.
Neophytou, A
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Mastorakos, E.
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Richardson, E.S.
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Stow, S.
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Zedda, M.
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11 September 2011
Neophytou, A
fc309e0b-20c4-4571-bf28-7f0c84017229
Mastorakos, E.
159653c4-33f6-4f4a-8f79-4751bfd4ba64
Richardson, E.S.
a8357516-e871-40d8-8a53-de7847aa2d08
Stow, S.
7c16869b-a5fc-42ab-9dab-30378815bfd4
Zedda, M.
40be8a72-bdc6-4f6b-a5bc-a5f947fe302d
Neophytou, A, Mastorakos, E., Richardson, E.S., Stow, S. and Zedda, M.
(2011)
A practical model for the high-altitude relight of a gas turbine combustor.
Seventh Mediterranean Combustion Symposium (MCS-7), Cagliari, Italy.
11 - 15 Sep 2011.
8 pp
.
Record type:
Conference or Workshop Item
(Paper)
Abstract
A model that simulates the possible flame trajectories following spark ignition in a generic recirculating flame has been applied to a realistic aero-engine combustor. The model has been previously validated for gaseous and simple spray flames. It uses a CFD solution of the un-ignited flow and estimates the volume of the combustor that could be ignited given a particular flow field, spray distribution, and spark location, shape and size, and also provides a measure of the variability between independent sparking events. From this information, the ease of igniting the combustor can be assessed, and hence the combustor and injector geometry and spark placement decisions can be informed at a very early stage of the design process. Results for igniting a Rolls-Royce test combustor run with kerosene at high-altitude relight conditions for which experimental data are available and for which a RANS CFD solution has been developed, demonstrate the usefulness of the model’s output. The results are consistent with experiment and also reveal that the spark characteristics and location used in the experiments, developed over a number of years by trial-and-error methods, are indeed close to optimum.
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Published date: 11 September 2011
Venue - Dates:
Seventh Mediterranean Combustion Symposium (MCS-7), Cagliari, Italy, 2011-09-11 - 2011-09-15
Organisations:
Aerodynamics & Flight Mechanics Group
Identifiers
Local EPrints ID: 384838
URI: http://eprints.soton.ac.uk/id/eprint/384838
PURE UUID: f0e6b6c5-9a79-4383-9cf2-915ff75be736
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Date deposited: 11 Jan 2016 12:32
Last modified: 15 Mar 2024 03:37
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Contributors
Author:
A Neophytou
Author:
E. Mastorakos
Author:
S. Stow
Author:
M. Zedda
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