Abstract
Design and Analysis of Gas Turbine Blade with Cooling
Highlights
The gas turbine blades are responsible for extracting energy from the high temperature, high pressure gas produced by the combustor
Aerofoil Selection and Modelling For this project, National Advisory Committee for Aeronautics (NACA) 4412 aerofoil is selected for turbine blade airfoil and its coordinates is taken from airfoil tools website
The blades are analysed for static thermal analysis and static structural analysis conditions
Summary
The gas turbine blades are responsible for extracting energy from the high temperature, high pressure gas produced by the combustor. The turbine blades are often the limiting component of gas turbines. To survive in this difficult environment, turbine blades often use exotic materials like super alloys and many different methods of cooling. Thermal efficiency of gas turbine still demands higher values of Turbine Entry Temperature (TET) without compromising on the structural integrity of the turbine components. The current TET level in advanced gas turbines is far above the melting point of the blade material. It is contingent to cool the turbine blades so that blade metal is within permissible metallurgical limits. Convection cooling is most widely used cooling concept in present day gas turbines. The coolant passes through small internal holes, leading to internal heat convection to cool the wall
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