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...
| Main Authors: | , |
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| Format: | Conference or Workshop Item |
| Language: | English English |
| Published: |
Institute of Physics Publishing
2018
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| Subjects: | |
| 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 |
| Summary: | 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. |
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