Optimization Turbine Blade Cooling by Applying Jet Impingement Cooling Channels

Abstract The aim of this paper is to optimize turbine blade cooling channels by applying jet impingement Method. selection experiment data for NASA 3CX blade, and 3D model using solidworks software create computational fluid dynamics (CFD) simulations used the coolant flow temperature distribution in vane, while experimental testing can validate CFD results provide additional insights into system's performance., ANSYS FLUENT code was as a solver, ICEM-CFD mesh generation. MATLAB calculation helpful simulations. Heat transfer conjugation analysis bases SST shear stress analyses K-ω turbulent model. conclude that providing information about how they differ studies being compared. demonstrate channels' hydraulic diameter decreases significant percentage (up 49.70%–69.55%) are drawn trailing edge blade. This have impact on heat coefficients performance system. pressure side observed follow Hylton Model, current study predicts large over-anticipated coefficient around Turbine head bulk suction side. In terms average coefficient, two models 23.36%. authors found effectiveness Optimized 0.4892 whole compared it with optimized model, which 0.6936, comparison between base suggest has significantly higher effectiveness. increase 29.46% 28.823% indicates design provides improved performance. These highlight importance considering designs blades maintain efficient safe operation.