Author : Shivani Pande, Amit Kumar Pal and Ruby Pant

One of the major sources of the stress arising in the turbo-machinery blades are the centrifugal and thermal loads acting at any section of the airfoil. Accounting for this phenomena stress evaluation of the blade attachment region in the disc has to be performed in order to avoid blade failure. Turbo-machinery blades are generally twisted, and the cross-section area varies from root to tip. The blade root shape at the attachment region is of much concern. Stress concentrations are predictable at this contact region. Therefore, a Comprehensive three-dimensional finite element study is made of the effect of the critical geometric features and interface conditions in the fir–tree region of a gas turbine disc upon the structural integrity. The aspects of the work were accordingly examined:- The first was concerned with the modeling of the three dimensional model on software PRO-E, and the second was concerned with the structural analysis of the geometry and examining the various stress distribution on the male and female assemblies of turbine assembly,

Keywords: Stress Analysis, Finite Element Method, Gas turbine blade, Fir-Tree joint.

Article published in International Journal of Current Engineering and Technology, Vol.6, No.4 (Aug-2016)