Cooling of turbine blade suction tip rail

• US 7,704,047 B2
• Filed: 11/21/2006
• Issued: 04/27/2010
• Est. Priority Date: 11/21/2006
• Status: Active Grant

• Current Assignee: Siemens Energy Incorporated (Siemens AG)
• Original Assignee: Siemens Energy Incorporated (Siemens AG)
• Inventors: Mathews, Ralph Warren, Liang, George
• Primary Examiner(s): Nguyen; Ninh H
• Application Number:
  US11/602,683
• Publication Number:
  US 20080118367A1
• Time in Patent Office: 1,253 Days
• Field of Search: 416/92, 416/96.R, 416/97.R, 415/115
• US Class Current: 416/97.00R
• CPC Class Codes: F01D 11/08 for sealing space between rotor blade tips and stator specially-shaped blade tips therefor F01D5/20
• CPC Class Codes: F01D 5/186 Film cooling F01D5/187 takes precedence
• CPC Class Codes: F01D 5/20 Specially-shaped blade tips to seal space between tips and stator F01D5/225 takes precedence
• CPC Class Codes: F05D 2240/55 Seals
• CPC Class Codes: F05D 2260/202 by film cooling
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A turbine blade including an airfoil, the airfoil including an airfoil outer wall having pressure and suction sidewalls joined together at chordally spaced apart leading and trailing edges extending radially outwardly from a blade root to a blade tip surface. A continuous squealer tip rail extends radially outwardly from and substantially continuously around the blade tip surface forming a radially outwardly open squealer pocket. The squealer tip rail includes an aft portion adjacent to the trailing edge, where the pressure side tip rail is discontinued in the chordal location of the aft portion. A plurality of chordally spaced film cooling holes are provided in a surface of the suction sidewall and provides a cooling fluid flow along the aft portion of the squealer tip rail surface to define a sub-boundary layer or film of cooling fluid between a hot gas vortex flow and the aft portion of the squealer tip rail at the suction sidewall.

Claims

1. A turbine blade comprising:

an airfoil including an airfoil outer wall extending radially outwardly from a blade root;

a blade tip surface located at an end of said airfoil distal from said root, and including pressure and suction sides joined together at chordally spaced apart leading and trailing edges of said airfoil;

a squealer tip rail extending radially outwardly from said blade tip surface and including an aft portion extending chordally between said leading edge and said trailing edge adjacent said trailing edge; and

a plurality of chordally spaced film cooling holes provided in a surface of said suction side and providing a flow of cooling fluid along said squealer tip rail surface at said suction side, wherein said film cooling holes are located in at least a portion of said squealer tip rail.

2. The blade of claim 1, wherein said cooling fluid exiting said film cooling holes form a film sub-boundary layer along said suction side, flowing in the same direction as a vortex flow formed by a hot fluid flow over said blade tip surface.

3. The blade of claim 2, wherein said film cooling holes are in communication with a cooling fluid circuit within said airfoil, said film cooling holes comprising shaped holes defined by diverging walls including said at least a portion of said squealer tip rail, extending in a downstream direction of cooling fluid flow, to form said film sub-boundary layer.

4. The blade of claim 1, wherein said film cooling holes are located adjacent said aft portion of said squealer tip rail.

5. The blade of claim 4, wherein said squealer tip rail comprises a pressure side tip rail and a suction side tip rail, said aft portion being formed as a continuation of said suction side tip rail.

6. The blade of claim 5, wherein said pressure side tip rail is discontinued in the chordal location of said aft portion.

7. The blade of claim 4, further including cooling holes in said airfoil outer wall adjacent an intersection of said outer wall and said pressure side of said blade tip surface at the chordal location of said aft portion.

8. The blade of claim 1, wherein said squealer tip rail extends substantially continuously around said blade tip surface forming a radially outwardly open squealer pocket.

9. The blade of claim 1, wherein said blade is a combustion gas turbine blade.

10. The blade of claim 1, wherein a centerline of each of said film cooling holes is slanted in a direction toward said trailing edge of said airfoil.

11. A turbine blade comprising:

an airfoil including an airfoil outer wall with pressure and suction sidewalls joined together at chordally spaced apart leading and trailing edges of said airfoil and extending radially outwardly from a blade root to a blade tip surface;

said blade tip surface including pressure and suction sides coinciding with said pressure and suction sidewalls;

a continuous squealer tip rail extending radially outwardly from and substantially continuously around said blade tip surface forming a radially outwardly open squealer pocket;

said squealer tip rail including an aft portion extending chordally between said leading edge and said trailing edge adjacent said trailing edge; and

a plurality of chordally spaced film cooling holes provided in a surface of said suction side and providing a flow of cooling fluid along said aft portion of said squealer tip rail surface at said suction side, wherein said film cooling holes are located in at least a portion of said squealer tip rail.

12. The blade of claim 11, wherein said cooling fluid exiting said film cooling holes form a film sub-boundary layer along said suction side.

13. The blade of claim 12, wherein said film cooling holes are in communication with a cooling fluid circuit within said airfoil, said film cooling holes comprising shaped holes defined by diverging walls including said at least a portion of said squealer tip rail, extending in a downstream direction of cooling fluid flow, to form said film sub-boundary layer.

14. The blade of claim 11, wherein said squealer tip rail comprises a pressure side tip rail and a suction side tip rail, said aft portion being formed as a continuation of said suction side tip rail.

15. The blade of claim 14, wherein said pressure side tip rail is discontinued in the chordal location of said aft portion.

16. The blade of claim 15, further including cooling holes in said airfoil outer wall adjacent an intersection of said outer wall and said pressure side of said blade tip surface at the chordal location of said aft portion.

17. A turbine blade comprising:

an airfoil including an airfoil outer wall with pressure and suction sidewalls joined together at chordally spaced apart leading and trailing edges of said airfoil and extending radially outwardly from a blade root to a blade tip surface;

said blade tip surface including pressure and suction sides coinciding with said pressure and suction sidewalls;

a continuous squealer tip rail extending radially outwardly from and substantially continuously around said blade tip surface forming a radially outwardly open squealer pocket;

said squealer tip rail including an aft portion extending chordally between said leading edge and said trailing edge adjacent said trailing edge; and

at least one film cooling hole in fluid communication with a cooling fluid circuit within said airfoil, said at least one film cooling hole comprising a shaped hole defined by diverging walls, extending in a downstream direction of cooling fluid flow, to form a film sub-boundary layer along said squealer tip rail surface at said suction side, wherein said at least one film cooling hole is located in at least a portion of said squealer tip rail and said diverging walls including at least a portion of said squealer tip rail.

18. The blade of claim 17, wherein said squealer tip rail comprises a pressure side tip rail and a suction side tip rail, said aft portion being formed as a continuation of said suction side tip rail.

19. The blade of claim 18, wherein said pressure side tip rail is discontinued in the chordal location of said aft portion.

20. The blade of claim 17, wherein said film sub-boundary layer formed by cooling fluid exiting said at least one film cooling hole flows in the same direction as a vortex flow formed by a hot fluid flow over said blade tip surface.