Evaluating the effects of multiple hole profiles on gas turbine blade cooling rate: a computational study.

The Gas turbines blade design and its modifications is a most crucial components towardsits sustainability against high temperature. The effective application of different cooling techniques enhances the heat transfer rate of these blades.The advent of modern manufacturing techniquesisnow days found more convenient in creation of micro cooling passages on the turbine blades. The profile variation of these micro cooling passages effects the heat transfer process. In this paper, a numerical study of convection cooling technique with different hole profile is performed for gas turbine blades using Computational technique. The square, triangular, and semi-circular hole profiles have been used to study its effect on the cooling efficiency.The effect of increasing the number of holes at different blade areas is also reported in this investigation.Adiabatic film cooling efficiency and heat transfer characteristics were observed using numerical analysis. The area near the trailing edge and on pressure and suction side edges are identified for the effect on overall heat transfer. A square hole with 11 number of holes has found higher Adiabatic film cooling efficiency (η_ad = 0.46) while the square hole with 17 number of holes found to be highest Adiabatic film cooling efficiency (η_ad) = 0.487 for 1400°Ctemperature.The computational analysis using CFD and ANSYS has registered the decrease in surface temperature of the blades. [ABSTRACT FROM AUTHOR]