A numerical investigation of geometric effects on pressure loss around 180° turning channels in a cooled turbine blade has been conducted. A base case was created for validation and to determine the optimum grid density, inlet boundary conditions, and turbulence model. For the base case, the channel maintains constant square cross-section geometry in both the inlet and outlet leg. After establishing the optimum criteria for the base case, the geometry of the outlet leg is altered from the standard square cross-section four ways. Two of the four altered geometries hold a constant area ratio, while the decline angles are changed to 6° and 12°. The final two geometries hold a constant decline angle of 6° while the area ratios are increased and decreased 20%. Using the optimum criteria found for the base case, models are run with the new geometries. As the angle of decline is increased the total pressure loss decreases slightly, while velocity magnitude plots indicate poor heat transfer characteristics near the inner wall due to flow separation. As the area ratio increases, total pressure loss decreases and velocity magnitude plots again indicate poor heat transfer characteristics. Thus, the geometry can effect the pressure loss by as much as 10%.

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