Determination of Thermal Stresses on Turbine Blades of Gas Turbine with NACA Airfoils By Finite Element Analysis


Authors : Anilkumar Konderu, Ganesh Purushothaman

Volume/Issue : Volume 2 - 2017, Issue 12 - December

Google Scholar : https://goo.gl/DF9R4u

Scribd : https://goo.gl/RinpoL

Thomson Reuters ResearcherID : https://goo.gl/3bkzwv

The compressor plays a vital role on jet engine as it concerns about the initial compression on engine bleed system and aircraft cooling. They are two types of compressor used in jet engine. They are axial compressor and centrifugal compressor. Here we discuss about the axial-flow compressor. As its major application were are in large gas turbine engines. This paper investigates the complications over the material selection, and temperature deformation that are majorly induced the stress deformations of blade in operating with different rps of 300 & 450, in the gas turbine engine. For this investigation, NACA6409, NACA64012 airfoils has been selected as base model and these are modelled by using CAD tool CATIA V5 and analysis had been done in ANSYS workbench 16.0, with two various materials viz. Nimonic 80A, Inconel 625.

Keywords : Jet Engine, Turbine Blade, Thermal Stress Deformation, NACA6409, NACA64012, Catia V5, Ansys Workbench 15.0, Nimonic 80A, Inconel 625.

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