Cooled gas turbine vane assembly

1. A gas turbine vane comprising:

an outer diameter pan affixed to an outer diameter platform, the outer diameter platform comprising:

a plurality of openings capable of receiving a plurality of cooling tubes;

an outer diameter platform trailing edge face spaced an axial distance from an outer diameter platform leading edge face;

a tube collar associated with the plurality of openings;

the plurality of cooling tubes extending radially inward from the outer diameter platform such that the tube collars are affixed to each of the plurality of cooling tubes and the corresponding opening;

a hollow airfoil extending radially inward from the outer diameter platform, the plurality of cooling tubes extending through the airfoil; and,

an inner diameter platform affixed to the hollow airfoil opposite the outer diameter platform such that the platforms are generally parallel to each other, the inner diameter platform comprising:

an inner diameter platform trailing edge face;

an inner diameter platform leading edge face;

a plurality of openings for receiving the plurality of cooling tubes;

a cover fixed to each of the plurality of cooling tubes proximate the inner diameter platform;

a forward pan affixed to a forward end of the inner diameter platform;

a plurality of film holes located in the inner diameter platform;

an aft cover affixed to an aft end of the inner diameter platform to form an aft cavity;

a meterplate affixed to the inner diameter platform adjacent to the forward pan, the meterplate having a plurality of holes located therein capable of restricting a cooling fluid flow to a desired pressure and mass flow for a region of the film holes positioned in the inner diameter platform and in fluid communication with the aft cavity;

an undercut located within the inner diameter platform, the undercut configured to reduce stiffness of the inner diameter platform.

2. The gas turbine vane of claim 1 , wherein the plurality of cooling tubes comprise a trailing edge tube, a mid-body tube, and a leading edge tube.

3. The gas turbine vane of claim 2 , wherein the plurality of cooling tubes each have a plurality of cooling holes located therein for directing a cooling fluid flow towards an inner wall of the airfoil.

4. The gas turbine vane of claim 1 , wherein the outer diameter pan includes a plurality of cooling holes.

5. The gas turbine vane of claim 1 , wherein the outer diameter platform, the airfoil and the inner diameter platform are a single part.

6. The gas turbine vane of claim 1 , where the outer diameter platform, the airfoil and the inner diameter platform are a welded assembly.

7. The gas turbine vane of claim 1 further comprising one or more sheet metal seals located within a slot in one or more side walls of the inner diameter platform and outer diameter platform.

8. The cooling circuit for a gas turbine vane of claim 1 , wherein the covers affixed to the end of the cooling tubes prevent the cooling fluid from flowing into the inner diameter platform of the gas turbine vane.

9. The gas turbine vane of claim 1 , wherein the undercut in the inner rail is located adjacent to a joint between the aft cover and the inner diameter platform.

10. A flow restriction device capable of controlling a cooling fluid to an aft portion of an inner diameter platform of a gas turbine vane comprising:

an aft cover fixed to the inner diameter platform forming an aft cavity;

a meterplate fixed to the inner diameter platform between a forward pan and the aft cover, the meterplate having a plurality of feed holes;

a plurality of film cooling holes located in the inner diameter platform and in fluid communication with the aft cavity;

wherein the cooling fluid is capable of passing through the feed holes of the meterplate, into the aft cavity, and through the plurality of film cooling holes.

11. The flow restriction device of claim 10 , wherein the aft cover is free of holes or perforations.

12. The flow restriction device of claim 11 , wherein the aft cover has a generally flat portion and three sidewalls.

13. The flow restriction device of claim 12 , wherein the aft cover is welded or brazed to the inner diameter platform.

14. The flow restriction device of claim 10 , wherein the meterplate is oriented generally perpendicular to the inner diameter platform so as to close an opening in the aft cavity while permitting a flow of the cooling fluid to enter the aft cavity generally parallel to the inner diameter platform.

15. The flow restriction device of claim 10 , wherein the plurality of film cooling holes are oriented at an acute angle relative to the inner diameter platform.

16. The flow restriction device of claim 10 , wherein the cooling fluid is compressed air or steam.

17. An inner diameter platform of a gas turbine vane capable of increased thermal deflection comprising:

a gas path surface separated from a cold surface by a platform thickness;

a forward pan and an aft cover fixed to the cold surface; and,

the platform thickness having an undercut extending a distance along a trailing edge face of the inner diameter platform and through a portion of the platform thickness such that the undercut reduces stiffness of the inner diameter platform adjacent to the aft cover.

18. The inner diameter platform of claim 17 , wherein the forward pan and aft cover are welded or brazed to the cold surface.

19. The inner diameter platform of claim 18 , wherein the undercut is located adjacent to a weld or braze joint between the aft cover and the cold surface of the inner diameter platform.

20. The inner diameter platform of claim 19 , wherein the undercut, relative to an axial centerline, is located radially outward of an inner rail of the inner diameter platform.