Design and Analysis of Gas Turbine Blade with Cooling

Authors

  • S. Dhivya Excel Engineering College
  • A. Karthikeyan Excel Engineering College

DOI:

https://doi.org/10.4108/eai.12-9-2018.155742

Keywords:

convective cooling, CATIA V5, ANSYS, Inconel, Nimonic, Thermal barrier coating, zirconia, yitria

Abstract

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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Published

12-09-2018

How to Cite

1.
Dhivya S, Karthikeyan A. Design and Analysis of Gas Turbine Blade with Cooling. EAI Endorsed Trans Energy Web [Internet]. 2018 Sep. 12 [cited 2024 Dec. 22];5(20):e12. Available from: https://publications.eai.eu/index.php/ew/article/view/964

Issue

Vol. 5 No. 20 (2018): EAI Endorsed Transactions on Energy Web and Information Technologies

Section

Research articles

License

Copyright (c) 2022 EAI Endorsed Transactions on Energy Web

Creative Commons License

This work is licensed under a Creative Commons Attribution 3.0 Unported License.

This is an open-access article distributed under the terms of the Creative Commons Attribution CC BY 4.0 license, which permits unlimited use, distribution, and reproduction in any medium so long as the original work is properly cited.

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