Paper Title
Thermal Analysis Of Aero Gas Turbine Blade

Abstract
The turbine entry temperature (TET) in gas turbine relates itself directly to the power output and the efficiency of the turbine. In present days gas turbines the TET exceed the melting temperature of the blade material. Advanced cooling technologies have resulted in high TET with acceptable material temperatures. At present an in house developed flow network code is used for cooling air mass flow distributions of the cooled blade based on internal flow elements pressure loss coefficients. In the present work, a typical stator blade with cooling techniques such as impingement, pin fins and film cooling are considered. Commercially available flow network software named Flowmaster is used to model the internal flow passage of blade and to estimate the flow distributions. Different types of flow elements in Flowmasterare used to model flow networks. Gas turbine module in Flowmaster is used for modelling the network. Blade is modelled into three sections to capture all internal flow geometries and the calculated flow rates are used to calculate the internal heat transfer coefficients and cooling air temperature rise due to heat transfer is estimated. Further 2-D FE model for five sections of the blade and a 3-D FE model of the blade is generated using Hypermesh and thermal analysis is carried out in ANSYS using macros programming for ease of boundary conditions application. Keywords— Turbine Entry Temperature, Blade cooling, Impingement cooling, Pin-fin cooling, Stator Blade, Flow network and Film cooling.