Abstract: The present invention is directed to a hollow turbine airfoil having a cooling system designed to provide enhanced cooling to the fillet of a turbine airfoil. The turbine airfoil may include at least one fillet cooling channel, passing proximate to the fillet. A portion of the fillet cooling channel may be positioned proximate to the fillet outer surface without breaching an outer surface of the turbine airfoil. The turbine airfoil may include a vortex plate positioned adjacent to the end wall inner surface proximate to the fillet and an opening of the fillet cooling channel may be in fluid communication with the vortex chamber. The turbine airfoil may also include at least one end wall film cooling channel that may extend obliquely through the end wall and may be in fluid communication with the vortex chamber.

Abstract: The present invention is directed to a hollow turbine airfoil having a cooling system designed to provide enhanced cooling to the fillet of a turbine airfoil. The turbine airfoil may include at least one fillet cooling channel, passing proximate to the fillet. A portion of the fillet cooling channel may be positioned proximate to the fillet outer surface without breaching an outer surface of the turbine airfoil. The turbine airfoil may include a vortex plate positioned adjacent to the end wall inner surface proximate to the fillet and an opening of the fillet cooling channel may be in fluid communication with the vortex chamber. The turbine airfoil may also include at least one end wall film cooling channel that may extend obliquely through the end wall and may be in fluid communication with the vortex chamber.

Abstract: A turbine fluid guide member (10) including an airfoil portion (12), a platform portion (14) and fillet (16) joining the airfoil portion to the platform portion. Fillet cooling holes (18a-18f) are positioned in the turbine fluid guide member relative to a pressure side vortex flow (22) so that a cooling fluid flow (20) exiting the hole is directed to form a cooling film (32) over the fillet. The cooling holes may be positioned in the airfoil portion, the platform portion, or any combination thereof, depending on the geometry of the airfoil and resultant vortex flows around the airfoil. A method of cooling a fillet of the turbine fluid guide member may include identifying a vortex flow around the fillet and selectively positioning a hole relative to the vortex flow such that a cooling fluid flow exiting the hole is directed to form a cooling film over the fillet.

Abstract: A turbine fluid guide member (10) including an airfoil portion (12), a platform portion (14) and fillet (16) joining the airfoil portion to the platform portion. Fillet cooling holes (18a-18f) are positioned in the turbine fluid guide member relative to a pressure side vortex flow (22) so that a cooling fluid flow (20) exiting the hole is directed to form a cooling film (32) over the fillet. The cooling holes may be positioned in the airfoil portion, the platform portion, or any combination thereof, depending on the geometry of the airfoil and resultant vortex flows around the airfoil. A method of cooling a fillet of the turbine fluid guide member may include identifying a vortex flow around the fillet and selectively positioning a hole relative to the vortex flow such that a cooling fluid flow exiting the hole is directed to form a cooling film over the fillet.

Abstract: An apparatus for cooling the trailing edge portion of a gas turbine vane. Two radially extending passages connected to the outer shroud direct cooling fluid to a plenum formed about mid-span adjacent the trailing edge. Two arrays of cooling fluid passages extend from the plenum. One array extends radially outward toward the outer shroud while the other array extends radially inward toward the inner shroud. The plenum distributes the cooling fluid to the two arrays of passages so that it flows radially inward and outward to manifolds formed in the inner and outer shrouds. The manifolds direct the spent cooling fluid to a discharge passage.