Numerical analysis of film cooling effectiveness using compound cooling holes at the end of gas turbine engine combustor

By using the well-known Bryton cycle, great turbine industries strive to extend the turbine inlet temperature and increase engine performance. However the turbine inlet temperature increment creates harsh environment for the downstream components of the combustor and so it is needed to design a cool...

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Main Author:	Salimi, Shahin
Format:	Thesis
Language:	English
Published:	2014
Subjects:	TJ Mechanical engineering and machinery
Online Access:	http://eprints.utm.my/id/eprint/78023/1/ShahihSalimiMFKM20141.pdf
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id	my-utm-ep.78023
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spelling	my-utm-ep.780232018-07-23T05:33:03Z Numerical analysis of film cooling effectiveness using compound cooling holes at the end of gas turbine engine combustor 2014-01 Salimi, Shahin TJ Mechanical engineering and machinery By using the well-known Bryton cycle, great turbine industries strive to extend the turbine inlet temperature and increase engine performance. However the turbine inlet temperature increment creates harsh environment for the downstream components of the combustor and so it is needed to design a cooling technique. The blowing ratio increase, caused to cooling effectiveness enhancement, however, for the traditional cooling system, the coolant not attached better on the surface at higher blowing ratios and therefore, it is required to restructure the cooling holes. Compound cooling holes is the useful way to this achievement. But, Most of the previous studies paid attention on the using compound cooling holes on the turbine blades and there is a lack of research on the application of these holes at the end wall of combustor. This study was accomplished in order to investigate the effects of cylindrical and row compound cooling holes with alignment angle of 30 degree, 60 degree and 90degree. The combustor used in the study is Pratt and Whitney gas turbine engine. This model was simulated and analyzed with a commercial finite volume package ANSYS FLUENT 14.0 to gain fundamental data.The entire findings of the study showed that with using the row compound cooling holes near the end wall surface, film cooling effectiveness is doubled compared to the cooling performance of baseline case. To conclude, as different arrangements of cooling holes affect the film cooling performance, it is strongly recommended to use a combination of compound cooling holes with different alignment angles for cooling panels. 2014-01 Thesis http://eprints.utm.my/id/eprint/78023/ http://eprints.utm.my/id/eprint/78023/1/ShahihSalimiMFKM20141.pdf application/pdf en public http://dms.library.utm.my:8080/vital/access/manager/Repository/vital:83171 masters Universiti Teknologi Malaysia, Faculty of Mechanical Engineering Faculty of Mechanical Engineering
institution	Universiti Teknologi Malaysia
collection	UTM Institutional Repository
language	English
topic	TJ Mechanical engineering and machinery
spellingShingle	TJ Mechanical engineering and machinery Salimi, Shahin Numerical analysis of film cooling effectiveness using compound cooling holes at the end of gas turbine engine combustor
description	By using the well-known Bryton cycle, great turbine industries strive to extend the turbine inlet temperature and increase engine performance. However the turbine inlet temperature increment creates harsh environment for the downstream components of the combustor and so it is needed to design a cooling technique. The blowing ratio increase, caused to cooling effectiveness enhancement, however, for the traditional cooling system, the coolant not attached better on the surface at higher blowing ratios and therefore, it is required to restructure the cooling holes. Compound cooling holes is the useful way to this achievement. But, Most of the previous studies paid attention on the using compound cooling holes on the turbine blades and there is a lack of research on the application of these holes at the end wall of combustor. This study was accomplished in order to investigate the effects of cylindrical and row compound cooling holes with alignment angle of 30 degree, 60 degree and 90degree. The combustor used in the study is Pratt and Whitney gas turbine engine. This model was simulated and analyzed with a commercial finite volume package ANSYS FLUENT 14.0 to gain fundamental data.The entire findings of the study showed that with using the row compound cooling holes near the end wall surface, film cooling effectiveness is doubled compared to the cooling performance of baseline case. To conclude, as different arrangements of cooling holes affect the film cooling performance, it is strongly recommended to use a combination of compound cooling holes with different alignment angles for cooling panels.
format	Thesis
qualification_level	Master's degree
author	Salimi, Shahin
author_facet	Salimi, Shahin
author_sort	Salimi, Shahin
title	Numerical analysis of film cooling effectiveness using compound cooling holes at the end of gas turbine engine combustor
title_short	Numerical analysis of film cooling effectiveness using compound cooling holes at the end of gas turbine engine combustor
title_full	Numerical analysis of film cooling effectiveness using compound cooling holes at the end of gas turbine engine combustor
title_fullStr	Numerical analysis of film cooling effectiveness using compound cooling holes at the end of gas turbine engine combustor
title_full_unstemmed	Numerical analysis of film cooling effectiveness using compound cooling holes at the end of gas turbine engine combustor
title_sort	numerical analysis of film cooling effectiveness using compound cooling holes at the end of gas turbine engine combustor
granting_institution	Universiti Teknologi Malaysia, Faculty of Mechanical Engineering
granting_department	Faculty of Mechanical Engineering
publishDate	2014
url	http://eprints.utm.my/id/eprint/78023/1/ShahihSalimiMFKM20141.pdf
_version_	1747817888411025408

Numerical analysis of film cooling effectiveness using compound cooling holes at the end of gas turbine engine combustor

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