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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my.iium.irep.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 |
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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/65970/1/65970_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 http://irep.iium.edu.my/65970/ http://iopscience.iop.org/article/10.1088/1757-899X/370/1/012022/meta |
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1643617667534290944 |
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13.18916 |