Numerical analysis of helical grooved channels near the leading edge region in gas turbine blade

Gas turbines are greatly operative engineered prime movers for transforming energy from thermal form (combustion stage) to mechanical form which is widely used for propulsion and power generation systems. The power output and thermal efficiency of gas turbine can be increased with increase in turbine inlet temperature of the hot gases. The modern gas turbines operating presently, the entry temperature of the hot gases at the inlet of the turbine are as high as 1723 K but this temperature surpasses the melting point of the turbine blade material. Since the present day gas turbines are functioning at very high temperatures, it is essential to implement effective cooling techniques, so the gas turbine vanes and blades sustain in the path of the hot fluid. Sufficient cooling cannot be achieved by passing the cool air through the blade, consequently it is essential to implement cooling methods that will additionally augment the heat transfer from the blade walls. It is seen that the blade can be cooled efficiently by adding in helical grooved channels near the leading edge region which promotes turbulence and higher flow rates through the channels. Based on the investigation better cooling of turbine blade is achieved by helical grooved channels with diameter five millimetre, pitch of helix: 50 millimetre and 8 starts resulting best thermal performance.