Cooling system for an airfoil vane
View Patent ↗A turbine vane for a turbine engine having a cooling system in inner aspects of the turbine vane. The cooling system includes one or more vortex forming chambers proximate to the intersection of an airfoil forming a portion of the turbine vane and an endwall to which the airfoil is attached. The intersection of the airfoil and the endwall may include a fillet for additional strength at the connection. The vortex forming chambers receive cooling fluids from cooling injection holes that provide a cooling fluid supply pathway between the cooling air supply cavity and the vortex forming chambers. The cooling fluids may be exhausted through one or more film cooling holes. The film cooling holes may exhaust cooling fluids proximate to the fillet to reduce the temperature of the external surface of the fillet and surrounding region.
1. A turbine vane, comprising:
a generally elongated airfoil having a leading edge, a trailing edge, a first endwall at a first end, a second endwall at a second end generally opposite the first end, at least one cavity forming a cooling system in the vane, and at least one outer wall defining the at least one cavity forming at least a portion of the cooling system;
wherein the cooling system comprises at least one vortex forming chamber in the outer wall of the vane that is located proximate to an intersection between the generally elongated airfoil and the first endwall for cooling the intersection between the generally elongated airfoil and the first endwall; and
wherein the at least one vortex forming chamber comprises at least one tube positioned around the perimeter of the generally elongated airfoil and proximate to the intersection between the generally elongated airfoil and the first endwall.
2. The turbine vane of claim 1 , wherein the at least one vortex forming chamber comprises at least one tube positioned around the perimeter of the generally elongated airfoil and proximate to the intersection between the generally elongated airfoil and the second endwall.
3. The turbine vane of claim 1 , wherein the at least one tube has a generally cylindrical cross-section.
4. A turbine vane, comprising:
a generally elongated airfoil having a leading edge, a trailing edge, a first endwall at a first end, a second endwall at a second end generally opposite the first end, and an internal cooling system formed from at least ones cavity defined in pert by at least one outer wall;
wherein the cooling system comprises at least one tubular vortex forming chamber in the outer wall of the vane that is located proximate to a fillet positioned at an intersection between the generally elongated airfoil and the first endwall for cooling the intersection between the generally elongated airfoil and the first endwall.
5. The turbine vane of claim 4 , wherein the at least one vortex forming chamber comprises at least one tube positioned around the perimeter of the generally elongated airfoil and proximate to the fillet at the intersection between the generally elongated airfoil and the first endwall.
6. The turbine vane of claim 5 , wherein the at least one vortex forming chamber comprises at least one tube positioned around the perimeter of the generally elongated airfoil and proximate to the fillet at the intersection between the generally elongated airfoil and the second endwall.
7. The turbine vane of claim 5 , wherein the at least one tube has a generally cylindrical cross-section.
8. The turbine vane of claim 4 , further comprising at least one cooling injection hole providing at least one cooling fluid supply pathway between the at least one cavity forming at least a portion of the cooling system and the at least one vortex forming chamber for enabling cooling fluids to enter the vortex forming chamber.
9. The turbine vane of claim 8 , wherein the at least one cooling injection hole directs cooling fluids into the vortex forming chamber in a direction offset from a longitudinal axis of the vortex forming chamber.
10. The turbine vane of claim 9 , wherein the at least one cooling injection hole comprises a plurality of cooling injection holes around a perimeter of the generally elongated airfoil.
11. The turbine vane of claim 4 , further comprising at least one film cooling hole extending from the at least one vortex forming chamber to an outer surface of the generally elongated airfoil.
12. The turbine vane of claim 11 , wherein an outlet of the at least one film cooling hole is positioned in the endwall proximate to the fillet position at the intersection between the generally elongated airfoil and the endwall.
13. A turbine vane, comprising:
a generally elongated airfoil having a leading edge, a trailing edge, a first endwall at a first end, a second endwall at a second end generally opposite the first end, at least one cavity forming a cooling system in the vane, and at least one outer wall defining the at least one cavity forming at least a portion of the cooling system;
wherein the cooling system comprises at least one vortex forming chamber in the outer wall of the vane that is located proximate to an intersection between the generally elongated airfoil and the first endwall for cooling the intersection between the generally elongated airfoil and the first endwall; and
at least one cooling injection hole providing at least one cooling fluid supply pathway between the at least one cavity forming at least a portion at the cooling system and the at least one vortex forming chamber for enabling cooling fluids to enter the vortex farming chamber.
14. The turbine vane of claim 13 , wherein the at least one cooling injection hole directs cooling fluids into the vortex forming chamber in a direction offset from a longitudinal axis at the vortex forming chamber.
15. The turbine vane of claim 14 , wherein the at least one cooling injection hole comprises a plurality of cooling injection holes around a perimeter of the generally elongated airfoil.
16. A turbine vane, comprising:
a generally elongated airfoil having a leading edge, a trailing edge, a first endwall at a first end, a second endwall at a second end generally opposite the first end, at least one cavity forming a cooling system in the vane, and at least one outer wall defining the at least one cavity forming at least a portion of the cooling system;
wherein the cooling system comprises at least one vortex forming chamber in the outer wall of the vane that is located proximate to an intersection between the generally elongated airfoil and the first endwall for cooling the intersection between the generally elongated airfoil and the first endwall; and
at least one film cooling hole extending from the at least one vortex forming chamber to an outer surface of the generally elongated airfoil.
17. The turbine vane of claim 16 , wherein an outlet of the at least one film cooling hole is positioned in the endwall proximate to the intersection between the generally elongated airfoil and the endwall.