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Analysis of the internal cooling system of a turbine blade Aerospace Engineering 2nd year Introduction The objective of this project is to present the CFD analysis of a turbine blade cooling systems to optimize airflow and achieve the lowest temperature drop possible to avoid melting of the blade. Three types of models were presented: 2D 3D Advanced 3D model The CFD analysis will be performed in ANSYS FLUENT. Model shapes 2D Model 3D Model Advanced 3D Model Each of the models has been given the same boundary conditions: Inlet velocity of 7m/s Inlet temperature of 250K Left and right wall temperature: 400K and 600K respectively Top wall temperature: 900K Analysis and conclusion The 3 models have been analyzed and they gave similar patterns in terms of velocity profile, which means that the fluid accelerated in the U-shape, where the corners of the system made the fluid to accelerate as well as the decrease of the cross sectional area, which takes place in the outlet. Changes of total, static and dynamic pressures happen whenever there is a velocity change. An increase in velocity caused an increase in dynamic pressure and a drop in static pressure, all according to Bernoulli’s principle. In 3D models the Valery Botsko, Caleb Handal, Hani Fardoun, Alberto Gonzalez Analysis of the internal cooling system of a turbine blade Aerospace Engineering 2nd year principle of no slip condition could be observed, which means zero velocity for the fluid whenever it is in contact with the surface. Velocity distribution Dynamic pressure distribution Static pressure distribution Temperature distribution The advanced model showed more heat transfer compared to other models, where the fluid behaved with more heat transfer taking place in the corners: Valery Botsko, Caleb Handal, Hani Fardoun, Alberto Gonzalez