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Aerodynamic study of combustor using axial 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 combustion intensity. Aerodynamically curved vanes all...

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Main Authors: Mohd. Jaafar, Mohammad Nazri, Mohd. Nor, Mohd. Khairul Firdaus, Ishak, Mohamad Shaiful Ashrull
Format: Article
Published: Praise Worthy Prize 2011
Subjects:
TJ Mechanical engineering and machinery
Online Access:http://eprints.utm.my/id/eprint/44718/
https://www.scopus.com/record/display.uri?eid=2-s2.0-79953164979&origin=resultslist&sort=plf-f&src=s&st1
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spelling my.utm.447182022-01-12T07:54:30Z http://eprints.utm.my/id/eprint/44718/ Aerodynamic study of combustor using axial swirler Mohd. Jaafar, Mohammad Nazri Mohd. Nor, Mohd. Khairul Firdaus Ishak, Mohamad Shaiful Ashrull TJ Mechanical engineering and machinery 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 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 was varied from 0.48, 0.83 and 1.43. The highest swirl number of 1.43 for axial swirler is capable to create a clear reversal mass flow rate zone. Praise Worthy Prize 2011 Article PeerReviewed Mohd. Jaafar, Mohammad Nazri and Mohd. Nor, Mohd. Khairul Firdaus and Ishak, Mohamad Shaiful Ashrull (2011) Aerodynamic study of combustor using axial swirler. International Review of Mechanical Engineering (IREME), 5 (1). pp. 92-99. ISSN 1970-8734 https://www.scopus.com/record/display.uri?eid=2-s2.0-79953164979&origin=resultslist&sort=plf-f&src=s&st1
institution Universiti Teknologi Malaysia
building UTM Library
collection Institutional Repository
continent Asia
country Malaysia
content_provider Universiti Teknologi Malaysia
content_source UTM Institutional Repository
url_provider http://eprints.utm.my/
topic TJ Mechanical engineering and machinery
spellingShingle TJ Mechanical engineering and machinery
Mohd. Jaafar, Mohammad Nazri
Mohd. Nor, Mohd. Khairul Firdaus
Ishak, Mohamad Shaiful Ashrull
Aerodynamic study of combustor using axial swirler
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 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 was varied from 0.48, 0.83 and 1.43. The highest swirl number of 1.43 for axial swirler is capable to create a clear reversal mass flow rate zone.
format Article
author Mohd. Jaafar, Mohammad Nazri
Mohd. Nor, Mohd. Khairul Firdaus
Ishak, Mohamad Shaiful Ashrull
author_facet Mohd. Jaafar, Mohammad Nazri
Mohd. Nor, Mohd. Khairul Firdaus
Ishak, Mohamad Shaiful Ashrull
author_sort Mohd. Jaafar, Mohammad Nazri
title Aerodynamic study of combustor using axial swirler
title_short Aerodynamic study of combustor using axial swirler
title_full Aerodynamic study of combustor using axial swirler
title_fullStr Aerodynamic study of combustor using axial swirler
title_full_unstemmed Aerodynamic study of combustor using axial swirler
title_sort aerodynamic study of combustor using axial swirler
publisher Praise Worthy Prize
publishDate 2011
url http://eprints.utm.my/id/eprint/44718/
https://www.scopus.com/record/display.uri?eid=2-s2.0-79953164979&origin=resultslist&sort=plf-f&src=s&st1
_version_ 1724073231331098624
score 13.211869

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