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 :

Scribd :

Thomson Reuters ResearcherID :

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.


Paper Submission Last Date
31 - May - 2023

Paper Review Notification
In 1-2 Days

Paper Publishing
In 2-3 Days

Video Explanation for Published paper

Never miss an update from Papermashup

Get notified about the latest tutorials and downloads.

Subscribe by Email

Get alerts directly into your inbox after each post and stay updated.

Subscribe by RSS

Add our RSS to your feedreader to get regular updates from us.