Design and Analysis of Gas Turbine Blade with Cooling
The turbine inlet temperature in advanced gas turbine engine is very high and it is above the melting point of blade material. In this project radial convective cooling method is used. The turbine blade with cooling holes (6, 8, 9,10, and 11) is designed using CATIA V5. The models are analyzed usin...
| Main Authors: | , |
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| Format: | Article |
| Language: | English |
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European Alliance for Innovation (EAI)
2018-09-01
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| Series: | EAI Endorsed Transactions on Energy Web |
| Subjects: | |
| Online Access: | https://publications.eai.eu/index.php/ew/article/view/964 |
| _version_ | 1811329602500427776 |
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| author | S. Dhivya A. Karthikeyan |
| author_facet | S. Dhivya A. Karthikeyan |
| author_sort | S. Dhivya |
| collection | DOAJ |
| description |
The turbine inlet temperature in advanced gas turbine engine is very high and it is above the melting point of blade material. In this project radial convective cooling method is used. The turbine blade with cooling holes (6, 8, 9,10, and 11) is designed using CATIA V5. The models are analyzed using the analysis package ANSYS to determine the thermal and structural behaviour by high temperature materials such as Inconel and Nimonic. The turbine has to be coated with ceramic coating (Zirconia) to improve the efficiency and power. The main role of Thermal Barrier Coating is to provide thermal insulation of the blade and reduce the need of blade of cooling and increase the creep life of the blade.
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| first_indexed | 2024-04-13T15:46:42Z |
| format | Article |
| id | doaj.art-8fabd4d75b90402b9e58cb13278a1672 |
| institution | Directory Open Access Journal |
| issn | 2032-944X |
| language | English |
| last_indexed | 2024-04-13T15:46:42Z |
| publishDate | 2018-09-01 |
| publisher | European Alliance for Innovation (EAI) |
| record_format | Article |
| series | EAI Endorsed Transactions on Energy Web |
| spelling | doaj.art-8fabd4d75b90402b9e58cb13278a16722022-12-22T02:40:58ZengEuropean Alliance for Innovation (EAI)EAI Endorsed Transactions on Energy Web2032-944X2018-09-0152010.4108/eai.12-9-2018.155742Design and Analysis of Gas Turbine Blade with CoolingS. Dhivya0A. Karthikeyan1Excel Engineering CollegeExcel Engineering College The turbine inlet temperature in advanced gas turbine engine is very high and it is above the melting point of blade material. In this project radial convective cooling method is used. The turbine blade with cooling holes (6, 8, 9,10, and 11) is designed using CATIA V5. The models are analyzed using the analysis package ANSYS to determine the thermal and structural behaviour by high temperature materials such as Inconel and Nimonic. The turbine has to be coated with ceramic coating (Zirconia) to improve the efficiency and power. The main role of Thermal Barrier Coating is to provide thermal insulation of the blade and reduce the need of blade of cooling and increase the creep life of the blade. https://publications.eai.eu/index.php/ew/article/view/964convective coolingCATIA V5ANSYSInconelNimonicThermal barrier coating |
| spellingShingle | S. Dhivya A. Karthikeyan Design and Analysis of Gas Turbine Blade with Cooling EAI Endorsed Transactions on Energy Web convective cooling CATIA V5 ANSYS Inconel Nimonic Thermal barrier coating |
| title | Design and Analysis of Gas Turbine Blade with Cooling |
| title_full | Design and Analysis of Gas Turbine Blade with Cooling |
| title_fullStr | Design and Analysis of Gas Turbine Blade with Cooling |
| title_full_unstemmed | Design and Analysis of Gas Turbine Blade with Cooling |
| title_short | Design and Analysis of Gas Turbine Blade with Cooling |
| title_sort | design and analysis of gas turbine blade with cooling |
| topic | convective cooling CATIA V5 ANSYS Inconel Nimonic Thermal barrier coating |
| url | https://publications.eai.eu/index.php/ew/article/view/964 |
| work_keys_str_mv | AT sdhivya designandanalysisofgasturbinebladewithcooling AT akarthikeyan designandanalysisofgasturbinebladewithcooling |