Impingement cooled bucket shroud, turbine rotor incorporating the same, and cooling method

• US 7,568,882 B2
• Filed: 01/12/2007
• Issued: 08/04/2009
• Est. Priority Date: 01/12/2007
• Status: Active Grant

• Current Assignee: GE Infrastructure Technology, LLC (GE Vernova, Inc.)
• Original Assignee: General Electric Company
• Inventors: Brittingham, Robert Alan, Arness, Brian Peter, Benjamin, Edward Durell
• Primary Examiner(s): Kershteyn; Igor
• Application Number:
  US11/652,483
• Publication Number:
  US 20080170946A1
• Time in Patent Office: 935 Days
• Field of Search: 415/1, 415/115, 415/116, 416/92, 416/97.R
• US Class Current: 415/1
• CPC Class Codes: F01D 5/187 Convection cooling
• CPC Class Codes: F01D 5/225 by shrouding
• CPC Class Codes: F05B 2240/33 Shrouds which are part of or which are rotating with the rotor
• CPC Class Codes: F05D 2260/201 by impingement of a fluid
• CPC Class Codes: F05D 2260/202 by film cooling
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A localized directional impingement cooling is used to reduce the metal temperatures on highly stressed regions of the tip shroud.

Claims

1. A turbine blade comprising:

a root portion for fixing said blade to a turbine rotor;

an airfoil portion extending longitudinally from said root;

at least one airfoil cooling passage extending through said airfoil, said airfoil cooling passage having an inlet for receiving a flow of cooling fluid;

a shroud projecting outwardly from said airfoil and having a radially inward facing surface and a radially outward facing surface;

a wall defining at least one exit hole for exiting cooling fluid from said airfoil cooling passage;

at least one shroud cooling chamber in flow communication with at least one said exit hole, said exit hole being directed towards a target wall surface of said cooling chamber, whereby said exit hole defines an impingement hole for impingement cooling said target wall surface as an impingement zone; and

at least one outlet aperture for flowing spent impingement cooling fluid out of said cooling chamber.

2. A turbine blade as in claim 1, comprising at least one plenum in flow communication with said airfoil cooling passage so as to receive cooling fluid therefrom, and wherein said wall is a wall of said plenum.

3. A turbine blade as in claim 2, wherein a total cross-sectional area of the exit holes from said plenum is less than a total cross-sectional area of the flow communication between the plenum and the airfoil cooling passage, whereby in-flow of cooling fluid pressurizes said at least one plenum.

4. A turbine blade as in claim 1, wherein said wall having said at least one exit hole is integrally formed with said shroud.

5. A turbine blade as in claim 1, wherein said target wall surface comprises an inner wall surface of a fillet between the airfoil and shroud.

6. A turbine blade as in claim 1, wherein said shroud has a bearing surface for engaging a shroud of an adjacent blade.

7. A turbine blade as in claim 3, wherein at least one said outlet aperture is disposed adjacent said bearing surface.

8. A turbine blade as in claim 2, wherein said plenum is comprised of a main plenum and an auxiliary plenum, and wherein said auxiliary plenum is in flow communication with said cooling chamber via an impingement plate having a plurality of impingement holes defined therethrough.

9. A turbine rotor having a row of turbine blades, at least one of said turbine blades comprising:

a root portion for fixing said blade to said turbine rotor;

an airfoil portion extending longitudinally from said root;

at least one airfoil cooling passage extending through said airfoil, said airfoil cooling passage having an inlet for receiving a flow of cooling fluid;

a shroud projecting outwardly from said airfoil and having a radially inward facing surface;

a wall defining at least one exit hole for exiting cooling fluid from said airfoil cooling passage;

at least one shroud cooling chamber in flow communication with at least one said exit hole, said exit hole being oriented to direct cooling fluid towards a target impingement zone, whereby said exit hole defines an impingement hole for impingement cooling said target impingement zone; and

at least one outlet opening for flowing spent impingement cooling fluid out of said cooling chamber.

10. A turbine rotor as in claim 9, comprising at least one plenum in flow communication with said airfoil cooling passage so as to receive cooling fluid therefrom, and wherein said wall is a wall of said plenum.

11. A turbine rotor as in claim 10, wherein a total cross-sectional area of the exit holes from said plenum is less than a total cross-sectional area of the flow communication between the plenum and the airfoil cooling passage, whereby in-flow of cooling fluid pressurizes said at least one plenum.

12. A turbine rotor as in claim 9, wherein said target impingement zone comprises an inner wall surface of a fillet between the airfoil and shroud.

13. A turbine rotor as in claim 9, wherein said plenum is in flow communication with said cooling chamber via a plurality of impingement holes in a partition wall therebetween.

14. A turbine rotor as in claim 9, wherein said shroud has a bearing surface for engaging a shroud of an adjacent blade in said row of turbine blades.

15. A turbine rotor as in claim 14, wherein at least one said outlet opening is disposed adjacent said bearing surface.

16. A turbine rotor as in claim 9, wherein there are a plurality of impingement cooling chambers defined in said shroud.

17. A turbine rotor as in claim 10, wherein said plenum is comprised of a main plenum and an auxiliary plenum, and wherein said auxiliary plenum is in flow communication with said cooling chamber via an impingement plate having a plurality of impingement holes defined therethrough.

18. A method of cooling a gas turbine airfoil having an associated substantially planar shroud extending in a plane substantially perpendicular to the airfoil, the method comprising:

a) providing at least one airfoil cooling passage in said airfoil;

b) providing at least one cooling chamber in said shroud;

c) directing cooling air from the at least one airfoil cooling passage through at least one impingement hole towards a wall surface of the at least one cooling chamber; and

d) directing spent impingement cooling air through at least one outlet opening in the cooling chamber.

19. The method of claim 18, wherein step d) is carried out by providing at least one cooling air exhaust hole in said shroud, opening at a peripheral edge of the shroud.

20. The method of claim 18, wherein at least one plenum is provided in the shroud, cooling air is supplied to said at least one plenum from said at least one airfoil cooling passage, and said impingement holes are defined in a wall of said at least one plenum.