Transonic Turbine Blade Tip Heat Transfer with Pressure Side Film Cooling

What is it about?

Investigated are spatially-resolved distributions of surface adiabatic film cooling effectiveness and surface heat transfer coefficients for a transonic turbine blade tip, with a unique and innovative film cooling arrangement, wherein a single row of five film cooling holes, located on the pressure-side of the blade very near to the blade tip, provides thermal protection to the blade tip.

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