Experimental and numerical investigation on gas turbine blade with the application of thermal barrier coatings

The engine parts material used in gas turbines (GTs) should be resistant to high-temperature variations. Thermal barrier coatings (TBCs) for gas turbine blades are found to have a significant effect on prolonging the life cycle of turbine blades by providing additional heat resistance. This work is...

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Main Authors:	Aabid, Abdul, Jyothi, J, Zayan, Jalal Mohammed, Khan, Sher Afghan
Format:	Article
Language:	English
Published:	Techno-Press 2019
Subjects:	TJ266 Turbines. Turbomachines (General)
Online Access:	http://irep.iium.edu.my/78803/ http://irep.iium.edu.my/78803/ http://irep.iium.edu.my/78803/ http://irep.iium.edu.my/78803/1/amr0804002.pdf

id	iium-78803
recordtype	eprints
spelling	iium-788032020-02-25T12:23:58Z http://irep.iium.edu.my/78803/ Experimental and numerical investigation on gas turbine blade with the application of thermal barrier coatings Aabid, Abdul Jyothi, J Zayan, Jalal Mohammed Khan, Sher Afghan TJ266 Turbines. Turbomachines (General) The engine parts material used in gas turbines (GTs) should be resistant to high-temperature variations. Thermal barrier coatings (TBCs) for gas turbine blades are found to have a significant effect on prolonging the life cycle of turbine blades by providing additional heat resistance. This work is to study the performance of TBCs on the high-temperature environment of the turbine blades. It is understood that this coating will increase the lifecycles of blade parts and decrease maintenance and repair costs. Experiments were performed on the gas turbine blade to see the effect of TBCs in different combinations of materials through the air plasma method. Three-layered coatings using materials INCONEL 718 as base coating, NiCoCrAIY as middle coating, and La2Ce2O7 as the top coating was applied. Finite element analysis was performed using a two-dimensional method to optimize the suitable formulation of coatings on the blade. Temperature distributions for different combinations of coatings layers with different materials and thickness were studied. Additionally, three-dimensional thermal stress analysis was performed on the blade with a commercial code. Results on the effect of TBCs shows a significant improvement in thermal resistance compared to the uncoated gas turbine blade. Techno-Press 2019-12 Article PeerReviewed application/pdf en http://irep.iium.edu.my/78803/1/amr0804002.pdf Aabid, Abdul and Jyothi, J and Zayan, Jalal Mohammed and Khan, Sher Afghan (2019) Experimental and numerical investigation on gas turbine blade with the application of thermal barrier coatings. Advances in Materials Research, 8 (4). pp. 275-293. ISSN 2234-0912 E-ISSN 2234-179X http://www.techno-press.org/content/?page=article&journal=amr&volume=8&num=4&ordernum=2 10.12989/amr.2019.8.4.275
repository_type	Digital Repository
institution_category	Local University
institution	International Islamic University Malaysia
building	IIUM Repository
collection	Online Access
language	English
topic	TJ266 Turbines. Turbomachines (General)
spellingShingle	TJ266 Turbines. Turbomachines (General) Aabid, Abdul Jyothi, J Zayan, Jalal Mohammed Khan, Sher Afghan Experimental and numerical investigation on gas turbine blade with the application of thermal barrier coatings
description	The engine parts material used in gas turbines (GTs) should be resistant to high-temperature variations. Thermal barrier coatings (TBCs) for gas turbine blades are found to have a significant effect on prolonging the life cycle of turbine blades by providing additional heat resistance. This work is to study the performance of TBCs on the high-temperature environment of the turbine blades. It is understood that this coating will increase the lifecycles of blade parts and decrease maintenance and repair costs. Experiments were performed on the gas turbine blade to see the effect of TBCs in different combinations of materials through the air plasma method. Three-layered coatings using materials INCONEL 718 as base coating, NiCoCrAIY as middle coating, and La2Ce2O7 as the top coating was applied. Finite element analysis was performed using a two-dimensional method to optimize the suitable formulation of coatings on the blade. Temperature distributions for different combinations of coatings layers with different materials and thickness were studied. Additionally, three-dimensional thermal stress analysis was performed on the blade with a commercial code. Results on the effect of TBCs shows a significant improvement in thermal resistance compared to the uncoated gas turbine blade.
format	Article
author	Aabid, Abdul Jyothi, J Zayan, Jalal Mohammed Khan, Sher Afghan
author_facet	Aabid, Abdul Jyothi, J Zayan, Jalal Mohammed Khan, Sher Afghan
author_sort	Aabid, Abdul
title	Experimental and numerical investigation on gas turbine blade with the application of thermal barrier coatings
title_short	Experimental and numerical investigation on gas turbine blade with the application of thermal barrier coatings
title_full	Experimental and numerical investigation on gas turbine blade with the application of thermal barrier coatings
title_fullStr	Experimental and numerical investigation on gas turbine blade with the application of thermal barrier coatings
title_full_unstemmed	Experimental and numerical investigation on gas turbine blade with the application of thermal barrier coatings
title_sort	experimental and numerical investigation on gas turbine blade with the application of thermal barrier coatings
publisher	Techno-Press
publishDate	2019
url	http://irep.iium.edu.my/78803/ http://irep.iium.edu.my/78803/ http://irep.iium.edu.my/78803/ http://irep.iium.edu.my/78803/1/amr0804002.pdf
first_indexed	2023-09-18T21:50:56Z
last_indexed	2023-09-18T21:50:56Z
_version_	1777413764381933568

Experimental and numerical investigation on gas turbine blade with the application of thermal barrier coatings

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