Gas turbine vane with integral cooling system
View Patent ↗A turbine vane usable in a turbine engine and having at least one cooling system. The cooling system includes three diffusors in an outer wall of the vane for reducing the velocity of the cooling fluids exiting the turbine vane. One of the diffusors is formed from one or more cavities in an outer wall of the turbine vane for heat dissipation. The cavities may be supplied with cooling fluids from an internal cooling cavity through one or more interior metering orifices. The cooling fluids may exit the cooling cavity through one or more exterior metering orifices, which are second diffusors, and diffusion slots, which are third diffusors, that reduce the velocity of the cooling fluids and enable formation of a film cooling layer on the outer surface of the turbine vane.
1. A turbine vane, comprising:
a generally elongated hollow airfoil formed from an outer wall having a leading edge, a trailing edge, a pressure side, a suction side, a first end adapted to be coupled to a hook attachment, a second end opposite the first end adapted to be coupled to an inner endwall, and a cooling system in the hollow airfoil formed from at least one internal cooling cavity;
a plurality of first diffusors, each formed from a plurality of cavities in the outer wall of the generally elongated hollow airfoil aligned spanwise into rows;
a plurality of interior metering orifices creating fluid pathways between the internal cooling cavity and the plurality of cavities in the outer wall forming the first diffusors, wherein at least one of the interior metering orifices is generally orthogonal relative to an inner surface of the outer wall;
a plurality of second diffusors, each formed from a plurality of exterior metering orifices creating fluid pathways between the plurality of cavities forming the first diffusors in the outer wall and an outer surface of the generally elongated hollow airfoil; and
wherein each of the first diffusors are formed from a linear flowpath in direct fluid communication with and aligned with a linear flow path of the second diffusors;
a third diffusor formed from a diffusion slot extending spanwise in the airfoil and coupled to the plurality of exterior metering orifices;
wherein the diffusion slot extends spanwise between adjacent sets of exterior metering slots at the outer surface of the generally elongated hollow airfoil, thereby placing the diffusion slot in fluid communication with a plurality of first diffusors.
2. The turbine vane of claim 1 , wherein at least one of the exterior metering orifices extends nonorthogonally from an outer surface of the outer wall to expel cooling fluid from the airfoil generally in a downstream direction.
3. The turbine vane of claim 1 , wherein the plurality of interior metering orifices comprise four generally cylindrical interior metering orifices in connection with each cavity in the outer wall of the hollow airfoil.
4. The turbine vane of claim 1 , wherein the exterior metering orifices comprise a generally bell shaped mouth at an outer surface of the outer wall.
5. The turbine vane of claim 1 , wherein the exterior metering orifices extend from side surfaces of the cavities in the outer wall of the hollow airfoil to the outer surface of the generally elongated hollow airfoil.
6. The turbine vane of claim 1 , wherein the plurality of cavities in rows are staggered in the spanwise direction in the airfoil.