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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:
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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:
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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