COOLED GAS TURBINE VANE ASSEMBLY

• US 20100129196A1
• Filed: 11/26/2008
• Published: 05/27/2010
• Est. Priority Date: 11/26/2008
• Status: Active Grant

• Current Assignee: H2 IP UK Limited
• Original Assignee: Alstom Limited (Alstom SA)
• Inventors: teRiele, Tim, Johnston, Chris, Bash, Gary, Parker, David, Strohl, James Page
• Granted Patent: US 8,142,137 B2
• Time in Patent Office: Days
• US Class Current: 415/115
• CPC Class Codes: F01D 5/188 with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall
• CPC Class Codes: F01D 5/189 the insert having a tubular cross-section, e.g. airfoil shape
• CPC Class Codes: F01D 9/041 using blades F01D5/148 takes precedence
• CPC Class Codes: F02C 7/12 Cooling of plants of component parts, see the relevant subclasses, e.g. F01D; cooling of engines in general F01P
• CPC Class Codes: F05D 2240/81 Cooled platforms
• CPC Class Codes: F05D 2260/202 by film cooling
• CPC Class Codes: Y10S 416/50 Vibration damping features

Abstract

A gas turbine vane to improve vane performance by addressing known failure mechanisms. A cooling circuit to the trailing edge of a vane airfoil is fed from the outer diameter platform, which prevents failure due to an oxidized and eroded airfoil trailing edge. The gas turbine includes an outer diameter platform, a hollow airfoil and an inner diameter platform with a plurality of cooling tubes extending radially through the airfoil. The cooling tubes are open at the outer diameter end and closed with covers at the inner diameter end. The inner diameter platform is also cooled and includes a meterplate for a portion of the cooling passageway and includes an undercut to improve thermal deflections of the inner diameter platform.

Claims

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 diameter platform extends along at least the trailing edge face of 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.