Enhancing Gas Turbine Blade Cooling Efficiency: A Computational Fluid Dynamics Study of Turbulator Impact

By using ANSYS Fluent Turbine, this study replicates the cooling of turbine blades.Simulate the symmetrical structure of the turbine blade cooling channel to simplify the problem model.The primary objective of this study is to characterize the fluid flow and heat transfer properties within the cooling blade channel.As a result, the model's simulation and boundary conditions are defined in such a way that the fluid behavior is concentrated on heat transfer.The cooling mechanism in this model is defined as cool airflow through an empty region in the blade's inner sides.The downstream wall is subjected to uniform heat flow, while the remainder of the wall is treated as an adiabatic surface.The flow had a Reynolds number (Re) range of 5,000 to 20,000.We solved the governing equations using the RNG k-turbulent model.The friction factor, Nusselt number, and skin friction are all affected by the turbulator height.The result indicates that the inclusion of a turbulator has a considerable effect on the cooling channel's performance.The presence of a turbulator within the cooling route increases the rate of heat transfer, and the increase is proportional to the form and size of the turbulator.When a trapezoidal turbulator was introduced into a smooth channel, the Nusselt number increased considerably.