Optimization of heat transfer on thermal barrier coated gas turbine blade

In the field of Aerospace Propulsion technology, material required to resist the maximum temperature. In this paper, using thermal barrier coatings (TBCs) method in gas turbine blade is used to protect hot section component from high-temperature effect to extend the service life and reduce the ma...

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Main Authors:	Aabid, Abdul, Khan, Sher Afghan
Format:	Conference or Workshop Item
Language:	English English
Published:	Institute of Physics Publishing 2018
Subjects:	TA401 Materials of engineering and construction TJ Mechanical engineering and machinery
Online Access:	http://irep.iium.edu.my/65970/ http://irep.iium.edu.my/65970/ http://irep.iium.edu.my/65970/ http://irep.iium.edu.my/65970/1/65970_Optimization%20of%20Heat%20Transfer%20on%20Thermal%20Barrier_conference%20article.pdf http://irep.iium.edu.my/65970/2/65970_Optimization%20of%20Heat%20Transfer%20on%20Thermal%20Barrier_scopus.pdf

id	iium-65970
recordtype	eprints
spelling	iium-659702018-08-29T04:25:00Z http://irep.iium.edu.my/65970/ Optimization of heat transfer on thermal barrier coated gas turbine blade Aabid, Abdul Khan, Sher Afghan TA401 Materials of engineering and construction TJ Mechanical engineering and machinery In the field of Aerospace Propulsion technology, material required to resist the maximum temperature. In this paper, using thermal barrier coatings (TBCs) method in gas turbine blade is used to protect hot section component from high-temperature effect to extend the service life and reduce the maintenance costs. The TBCs which include three layers of coating corresponding initial coat is super alloy-INCONEL 718 with 1 mm thickness, bond coat is Nano-structured ceramic-metallic composite-NiCoCrAIY with 0.15 mm thickness and top coat is ceramic composite-La2Ce2O7 with 0.09 mm thickness on the nickel alloy turbine blade which in turn increases the strength, efficiency and life span of the blades. Modeling a gas turbine blade using CATIA software and determining the amount of heat transfer on thermal barrier coated blade using ANSYS software has been performed. Thermal stresses and effects of different TBCs blade base alloys are considered using CATIA and ANSYS. Institute of Physics Publishing 2018-06-01 Conference or Workshop Item PeerReviewed application/pdf en http://irep.iium.edu.my/65970/1/65970_Optimization%20of%20Heat%20Transfer%20on%20Thermal%20Barrier_conference%20article.pdf application/pdf en http://irep.iium.edu.my/65970/2/65970_Optimization%20of%20Heat%20Transfer%20on%20Thermal%20Barrier_scopus.pdf Aabid, Abdul and Khan, Sher Afghan (2018) Optimization of heat transfer on thermal barrier coated gas turbine blade. In: 1st International Conference on Aerospace and Mechanical Engineering, AeroMech 2017, 21 -22 November 2017, Parkroyal HotelBatu Ferringhi, Penang; Malaysia. http://iopscience.iop.org/article/10.1088/1757-899X/370/1/012022/meta 10.1088/1757-899X/370/1/012022
repository_type	Digital Repository
institution_category	Local University
institution	International Islamic University Malaysia
building	IIUM Repository
collection	Online Access
language	English English
topic	TA401 Materials of engineering and construction TJ Mechanical engineering and machinery
spellingShingle	TA401 Materials of engineering and construction TJ Mechanical engineering and machinery Aabid, Abdul Khan, Sher Afghan Optimization of heat transfer on thermal barrier coated gas turbine blade
description	In the field of Aerospace Propulsion technology, material required to resist the maximum temperature. In this paper, using thermal barrier coatings (TBCs) method in gas turbine blade is used to protect hot section component from high-temperature effect to extend the service life and reduce the maintenance costs. The TBCs which include three layers of coating corresponding initial coat is super alloy-INCONEL 718 with 1 mm thickness, bond coat is Nano-structured ceramic-metallic composite-NiCoCrAIY with 0.15 mm thickness and top coat is ceramic composite-La2Ce2O7 with 0.09 mm thickness on the nickel alloy turbine blade which in turn increases the strength, efficiency and life span of the blades. Modeling a gas turbine blade using CATIA software and determining the amount of heat transfer on thermal barrier coated blade using ANSYS software has been performed. Thermal stresses and effects of different TBCs blade base alloys are considered using CATIA and ANSYS.
format	Conference or Workshop Item
author	Aabid, Abdul Khan, Sher Afghan
author_facet	Aabid, Abdul Khan, Sher Afghan
author_sort	Aabid, Abdul
title	Optimization of heat transfer on thermal barrier coated gas turbine blade
title_short	Optimization of heat transfer on thermal barrier coated gas turbine blade
title_full	Optimization of heat transfer on thermal barrier coated gas turbine blade
title_fullStr	Optimization of heat transfer on thermal barrier coated gas turbine blade
title_full_unstemmed	Optimization of heat transfer on thermal barrier coated gas turbine blade
title_sort	optimization of heat transfer on thermal barrier coated gas turbine blade
publisher	Institute of Physics Publishing
publishDate	2018
url	http://irep.iium.edu.my/65970/ http://irep.iium.edu.my/65970/ http://irep.iium.edu.my/65970/ http://irep.iium.edu.my/65970/1/65970_Optimization%20of%20Heat%20Transfer%20on%20Thermal%20Barrier_conference%20article.pdf http://irep.iium.edu.my/65970/2/65970_Optimization%20of%20Heat%20Transfer%20on%20Thermal%20Barrier_scopus.pdf
first_indexed	2023-09-18T21:33:37Z
last_indexed	2023-09-18T21:33:37Z
_version_	1777412674215215104

Optimization of heat transfer on thermal barrier coated gas turbine blade

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