Gas Turbine Blade with Cooling Holes
This case represents airflow through a rotationally periodic gas-turbine stator. The stator guide vanes are film-cooled with four rows of film cooling holes in the leading edge region of the vanes (showerhead film-cooling). There are 80 holes in total. The coolant is supplied by a straight tube perpendicular to the main flow. There are 28 blades circumferentially, but only one blade is modeled along with periodic boundary conditions. The multiple cavities in the geometry present substantial challenges in the generation. Multi-zone grid generation was performed using CENTAUR, resulting in a total of 482K prisms, 1M tetrahedra and 443K nodes.
Preliminary flow simulations have been performed on this geometry.