ENHANCING THE THERMAL EFFICIENCY OF GAS TURBINE BLADE

Abstract

For gas turbines, aircraft propulsion, soil-based power production and industrial applications are widely used.
Improved thermal efficiency of the gas turbine by increasing turbine input temperature. The current rotor intake
temperature in the advanced gas turbine is above the melting point of the blade. For continuous safe operation of
high-performance gas turbines, a sophisticated cooling system must be devised. Outdoor and indoor gas turbines are
cooled. Various techniques of cooling blades and vanes have been suggested. The strategies used in the cooling of
blades and vanes are to have radial hole to flow through high-speed cooling air.
In this paper a turbine blade in CREO parametric software has been created and modelled. The blades of the turbines
are cooled using film. There are 3 holes, 7 holes, 13 holes modelled on the turbine blade with the film cooling for no
holes.
The heat transfer rates, heat transfer coefficients of the blade are determined from the thermal analysis. Chromium
steel is the present material used for blading and it is substituted by nickel alloys in this paper. CFD analysis,
ANSYS is used for thermal analysis