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Combustor aerodynamic using radial swirler

A study has been conducted to investigate the flow pattern in a gas turbine combustion chamber by simulation and experimental approaches. Flow pattern inside a combustor is important to self sustain the flame, increase mixing of air and fuel, and increase combustion intensity. Aerodynamically curved...

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Main Authors: Mohd Jaafar, Mohammad Nazri, Jusoff, Kamaruzaman, Osman, Mohamed Seroleh, Ishak, Mohamad Shaiful Ashrul
Format: Article
Language:English
Published: Academic Journals 2011
Online Access:http://psasir.upm.edu.my/id/eprint/23903/1/23903.pdf
http://psasir.upm.edu.my/id/eprint/23903/
https://academicjournals.org/journal/IJPS/article-abstract/37FFA0E21370
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spelling my.upm.eprints.239032020-07-07T01:23:41Z http://psasir.upm.edu.my/id/eprint/23903/ Combustor aerodynamic using radial swirler Mohd Jaafar, Mohammad Nazri Jusoff, Kamaruzaman Osman, Mohamed Seroleh Ishak, Mohamad Shaiful Ashrul A study has been conducted to investigate the flow pattern in a gas turbine combustion chamber by simulation and experimental approaches. Flow pattern inside a combustor is important to self sustain the flame, increase mixing of air and fuel, and increase combustion intensity. Aerodynamically curved vanes allow the incoming axial flow to turn gradually. This inhibits flow separation on the suction side of the vane. Thus, more complete turning and higher swirl and radial-velocity components can be generated at the swirler exit with the added advantage of lower pressure loss. The swirl number varied from 0.49, 1.29 and 2.29 for flat vanes and only 1.57 for curved vane. The highest swirl number of 2.29 for flat vane and 1.57 for curve vane are capable of creating a clear reversal mass flow rate zone and higher swirl strength reduces the corner recirculation zone size and hence reduces the negative impact on the combustion process and the homogeneity of the wall temperature as well. Further investigation can be done for higher swirl number for both types of swirler. Academic Journals 2011-07-04 Article PeerReviewed text en http://psasir.upm.edu.my/id/eprint/23903/1/23903.pdf Mohd Jaafar, Mohammad Nazri and Jusoff, Kamaruzaman and Osman, Mohamed Seroleh and Ishak, Mohamad Shaiful Ashrul (2011) Combustor aerodynamic using radial swirler. International Journal of the Physical Sciences, 6 (13). art. no. 37FFA0E21370. pp. 3091-3098. ISSN 1992-1950 https://academicjournals.org/journal/IJPS/article-abstract/37FFA0E21370 10.5897/IJPS11.404
institution Universiti Putra Malaysia
building UPM Library
collection Institutional Repository
continent Asia
country Malaysia
content_provider Universiti Putra Malaysia
content_source UPM Institutional Repository
url_provider http://psasir.upm.edu.my/
language English
description A study has been conducted to investigate the flow pattern in a gas turbine combustion chamber by simulation and experimental approaches. Flow pattern inside a combustor is important to self sustain the flame, increase mixing of air and fuel, and increase combustion intensity. Aerodynamically curved vanes allow the incoming axial flow to turn gradually. This inhibits flow separation on the suction side of the vane. Thus, more complete turning and higher swirl and radial-velocity components can be generated at the swirler exit with the added advantage of lower pressure loss. The swirl number varied from 0.49, 1.29 and 2.29 for flat vanes and only 1.57 for curved vane. The highest swirl number of 2.29 for flat vane and 1.57 for curve vane are capable of creating a clear reversal mass flow rate zone and higher swirl strength reduces the corner recirculation zone size and hence reduces the negative impact on the combustion process and the homogeneity of the wall temperature as well. Further investigation can be done for higher swirl number for both types of swirler.
format Article
author Mohd Jaafar, Mohammad Nazri
Jusoff, Kamaruzaman
Osman, Mohamed Seroleh
Ishak, Mohamad Shaiful Ashrul
spellingShingle Mohd Jaafar, Mohammad Nazri
Jusoff, Kamaruzaman
Osman, Mohamed Seroleh
Ishak, Mohamad Shaiful Ashrul
Combustor aerodynamic using radial swirler
author_facet Mohd Jaafar, Mohammad Nazri
Jusoff, Kamaruzaman
Osman, Mohamed Seroleh
Ishak, Mohamad Shaiful Ashrul
author_sort Mohd Jaafar, Mohammad Nazri
title Combustor aerodynamic using radial swirler
title_short Combustor aerodynamic using radial swirler
title_full Combustor aerodynamic using radial swirler
title_fullStr Combustor aerodynamic using radial swirler
title_full_unstemmed Combustor aerodynamic using radial swirler
title_sort combustor aerodynamic using radial swirler
publisher Academic Journals
publishDate 2011
url http://psasir.upm.edu.my/id/eprint/23903/1/23903.pdf
http://psasir.upm.edu.my/id/eprint/23903/
https://academicjournals.org/journal/IJPS/article-abstract/37FFA0E21370
_version_ 1672612177650909184
score 13.211869

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