Research Article
Design and Analysis of Gas Turbine Blade with Cooling
@ARTICLE{10.4108/eai.12-9-2018.155742, author={S. Dhivya and A. Karthikeyan}, title={Design and Analysis of Gas Turbine Blade with Cooling}, journal={EAI Endorsed Transactions on Energy Web and Information Technologies}, volume={5}, number={20}, publisher={EAI}, journal_a={EW}, year={2018}, month={9}, keywords={convective cooling, CATIA V5, ANSYS, Inconel, Nimonic, Thermal barrier coating, zirconia, yitria}, doi={10.4108/eai.12-9-2018.155742} }- S. Dhivya
A. Karthikeyan
Year: 2018
Design and Analysis of Gas Turbine Blade with Cooling
EW
EAI
DOI: 10.4108/eai.12-9-2018.155742
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.
Copyright © 2018 S. Dhivya et al., licensed to EAI. This is an open access article distributed under the terms of the Creative Commons Attribution licence (http://creativecommons.org/licenses/by/3.0/), which permits unlimited use, distribution and reproduction in any medium so long as the original work is properly cited.