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 is performed, resulting in a total of 482K prisms, 1,000K tetrahedra and 443K nodes.

Preliminary flow simulations have been performed on this geometry.

 

Velocity vectors and particle traces emerging from the cooling holes

 

Different views of the hybrid grid

Velocity Vectors and Particle Traces Emerging from the Cooling Holes of the Gas Turbine Blade Geometry

Different Views of the Hybrid Grid for the Gas Turbine Blade Geometry With Cooling Holes

View	Mesh
Surface
Closeup of Surface Mesh
Surface Mesh for Cooling Holes
Cutaway View of the Prismatic Mesh
Hybrid Mesh

The final grid contains:

   167454 Total Nodes
   670860 Total Elements
   110206 Prisms
     9206 Pyramids
   551448 Tetrahedra
     1464 Periodic Node Pairs
    41520 Total Boundary Faces
       11 Boundary Groups
           12558 faces in group:  Holes
             200 faces in group:  Inlet
             200 faces in group:  Outlet
            1869 faces in group:  Hub
            2056 faces in group:  Shroud
           11675 faces in group:  Blade
            8115 faces in group:  Cooling Pipe
            2136 faces in group:  Periodic
            2136 faces in group:  Shadow
             400 faces in group:  Tube Inlet
             175 faces in group:  Tube Outlet