Simulation of Gas Turbine Blades with Cooling Holes

Gas turbines are commonly used turbo-machine basically used in the power cycles which is operated by the gaseous fluid as a working medium. The gas turbine consists of impeller, casing, inlet and outlet duct, and nozzle also. The impeller is the rotating member of the gas turbine and blades are mounted on the periphery of the impeller. During the continuous flow of working medium on the blades, friction is generated and as a result of which blades are heated. Due to this heating action, the blades get deformed so, to avoid this deformation continuous cooling of the blades are mandatory. There are different techniques of cooling’s exists such as by external cooling medium either by air or water. To supply the cooling medium from outside is one of the tedious task to overcome this difficulty the cooling holes can be provided inside the blades at different locations, this cooling hole provides better heat transfer as well as good temperature distribution throughout the blade and it will be helpful to overcome the structural deformation of the blades up to a certain level. This, in turn, increases the blade life and enhances the performance of the blade. In present work, we will focus on the different designs of the blades with providing holes at different locations as well as the same is to be optimized for different blade material and provide a better choice for selecting a proper blade for a variety of applications.