Modelling Of Gas Turbine Rotor Blade with Internal Cooling Passages
Journal Title: International Journal for Research in Applied Science and Engineering Technology (IJRASET) - Year 2016, Vol 4, Issue 3
Abstract
Gas turbines are extensively used for land-based power generation, aircraft propulsion and industrial applications. The turbine blade temperature plays a critical role in developing the thermal efficiency and power output and lifetime of gas turbines. The rotor inlet temperature should be below the melting point of the turbine blade material. So the gas turbine blade needs “cooling technologies” to overcome the problem. This paper deals with the modelling and analysis of gas turbine rotor blade with internal cooling passages. The blade coordinate data is imported through the GSD_ExcelSplineLOft excel sheet to the CATIAV5 and modelled. FEA analysis and meshing both are done by using ANSYS. Internal cooling passages provided on blade tip, which passes through the axial length of the turbine blade. The coolant flows through these cooling passages to reduce the temperature distribution on the blade surface. Structural and thermal analyses have to be done to find out the temperature distribution over the surface of the turbine blade after applying coolant.
Authors and Affiliations
Ganesh Cheemanapalle, S Praveen Kumar, Sreenivasulu Bezawada
Keywords
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- EP ID EP21739
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