TURBINE BUCKET ANGEL WING FEATURES FOR FORWARD CAVITY FLOW CONTROL AND RELATED METHOD

• US 20130108441A1
• Filed: 10/26/2011
• Published: 05/02/2013
• Est. Priority Date: 10/26/2011
• Status: Active Grant

• Current Assignee: GE Infrastructure Technology, LLC (GE Vernova, Inc.)
• Original Assignee: General Electric Company
• Inventors: INGRAM, Clint Luigie
• Granted Patent: US 8,979,481 B2
• Time in Patent Office: Days
• US Class Current: 416/1
• CPC Class Codes: F01D 11/001 for sealing space between stator blade and rotor
• CPC Class Codes: F01D 11/04 using sealing fluid, e.g. steam

Abstract

A turbine bucket includes a radially inner mounting portion, a shank radially outward of the mounting portion, a radially outer airfoil and a substantially planar platform radially between the shank, and the airfoil. At least one axially-extending angel wing seal flange is formed on a leading end of the shank forming a circumferentially extending trench cavity along the leading edge of the shank, radially between an underside of the platform leading edge and the angel wing seal flange. A plurality of substantially radially-extending purge air holes are formed in the angel wing seal flange, adapted to fluidly connect a turbine rotor wheel space cavity with the trench cavity and thereby supply purge air to the outer surface of the angel wing seal flange.

Claims

1. A turbine bucket comprising a radially inner mounting portion, a shank radially outward of the mounting portion, a radially outer airfoil and a substantially planar platform radially between the shank and the airfoil;

at least one axially-extending angel wing seal flange on a leading end of the shank forming a circumferentially extending trench cavity along the leading end of the shank, radially between an underside of a platform leading edge and the angel wing seal flange; and

a plurality of substantially radially-extending purge air holes formed in said angel wing seal flange, adapted to fluidly connect a turbine rotor wheel space cavity with said trench cavity and thereby supply purge air to the outer surface of said angel wing seal flange.

2. The turbine bucket of claim 1 wherein said plurality of substantially radially-extending purge air holes have outlets located closely adjacent an interface between said angel wing seal flange and said shank.

3. The turbine bucket of claim 1 wherein said plurality of substantially radially-extending purge air holes are slanted axially toward said shank.

4. The turbine bucket of claim 3 wherein said plurality of substantially radially-extending purge air holes are slanted in a circumferential direction.

5. The turbine bucket of claim 1 wherein said plurality of substantially radially-extending purge air holes are substantially uniformly distributed in a circumferential direction.

6. The turbine bucket of claim 2 wherein said plurality of substantially radially-extending purge air holes are substantially uniformly distributed in a circumferential direction.

7. The turbine bucket of claim 1 wherein said plurality of substantially radially-extending purge air holes are substantially non-uniformly distributed in a circumferential direction.

8. The turbine bucket of claim 2 wherein said plurality of substantially radially-extending purge air holes are substantially non-uniformly distributed in a circumferential direction.

9. The turbine bucket of claim 2 wherein said plurality are slanted toward said shank in a radially-outward direction, and also slanted in a circumferential direction.

10. The turbine bucket of claim 1 wherein said platform is formed with a substantially straight leading edge.

11. The turbine bucket of claim 1 wherein said platform is formed with a scalloped leading edge.

12. A turbine wheel supporting a circumferentially arranged row of buckets, each bucket comprising a radially inner mounting portion, a shank radially outward of the mounting portion, at least one radially outer airfoil and a substantially planar platform radially between the shank and the airfoil;

at least one axially-extending angel wing seal flange on a leading end of the shank forming a circumferentially extending trench cavity along the leading end of the shank, radially between an underside of a platform leading edge and the angel wing seal flange;

and wherein a plurality of substantially radially-extending purge air holes are formed in said angel wing seal flange, adapted to connect a turbine rotor wheel space cavity with said trench cavity.

13. The turbine wheel of claim 12 wherein said plurality of substantially radially-extending purge air holes are located closely adjacent an interface between said angel wing seal flange and said shank.

14. The turbine wheel of claim 12 wherein said plurality of said substantially radially-extending purge air holes are axially slanted toward said shank.

15. The turbine wheel of claim 14 wherein said plurality of purge air holes are slanted in a circumferential direction.

16. The turbine wheel of claim 12 wherein said plurality of cooling holes are substantially uniformly distributed in a circumferential direction.

17. The turbine wheel of claim 12 wherein said plurality of substantially radially-extending purge air holes are axially slanted toward said shank in a radially-outward direction and also slanted in a circumferential direction.

18. The turbine wheel of claim 12 wherein said platform is formed with a substantially straight leading edge.

19. A method of controlling secondary flow at a radial gap between a rotating turbine disk mounting a plurality of buckets and an adjacent nozzle, the method comprising:

(a) locating at least one angel wing seal on a leading end of each of said plurality of buckets extending axially toward said nozzle to thereby form a barrier between a hot stream of combustion gases on a radially outer side of said angel wing seal and purge air in a wheel space radially inward of said at least one angel wing seal; and

(b) providing plural openings in said angel wing seal enabling purge air to flow into an area radially outward of said angel wing seal flange to thereby prevent the combustion gases from impinging on said angel wing seal flange.

20. The method of claim 19 wherein said plural openings are slanted axially toward said bucket in a radially outward direction and also slanted in a circumferential direction.