Trailing edge cooling for turbine blade airfoil

• US 8,096,770 B2
• Filed: 03/03/2009
• Issued: 01/17/2012
• Est. Priority Date: 09/25/2008
• Status: Active Grant

• Current Assignee: Siemens Energy Incorporated (Siemens AG)
• Original Assignee: Siemens Energy Incorporated (Siemens AG)
• Inventors: Liang, George
• Primary Examiner(s): MAI, ANH D
• Application Number:
  US12/396,629
• Publication Number:
  US 20100074762A1
• Time in Patent Office: 1,050 Days
• Field of Search: 416/97.R, 415/115
• US Class Current: 416/97.R
• CPC Class Codes: F01D 5/186 Film cooling F01D5/187 takes precedence
• CPC Class Codes: F05D 2240/122 related to the trailing edge of a stator vane
• CPC Class Codes: F05D 2240/304 related to the trailing edge of a rotor blade
• CPC Class Codes: F05D 2250/141 circular
• CPC Class Codes: F05D 2260/2212 by creating turbulence vortex generators, turbulators or the like for mixing F05D2240/127
• CPC Class Codes: F05D 2260/22141 using fins or ribs

Abstract

A gas turbine engine hollow turbine airfoil having chordwise spaced apart leading and trailing edges, and widthwise spaced apart pressure and suction sidewalls extending chordwise between the leading edge and the trailing edge. A trailing edge rib extends from the trailing edge toward the leading edge, and forms a solid member between the pressure and suction sidewalls. A cooling fluid channel extends in the spanwise direction through the airfoil adjacent to the trailing edge rib. A plurality of fluid chambers are formed in the trailing edge rib. Film cooling holes extend from the fluid chambers to the pressure and suction sidewalls, and trailing edge discharge holes extend from the fluid chambers to the trailing edge. A metering hole is associated with each of the fluid chambers to define a flow restriction connecting the cooling fluid channel to a respective fluid chamber.

Claims

1. A gas turbine engine hollow turbine airfoil comprising:

an outer wall surrounding a hollow interior;

said outer wall extending radially outwardly in a spanwise direction from an airfoil platform to an airfoil tip and having chordwise spaced apart leading and trailing edges, and widthwise spaced apart pressure and suction sidewalls extending chordwise between said leading edge and said trailing edge;

a trailing edge rib extending from said trailing edge toward said leading edge, said trailing edge rib forming a solid member between said pressure and suction sidewalls;

a cooling fluid channel extending in the spanwise direction through said airfoil adjacent to said trailing edge rib;

a plurality of fluid chambers formed in said trailing edge rib and extending chordwise between said cooling fluid channel and said trailing edge;

a plurality of film cooling holes extending from said fluid chambers to said pressure and suction sidewalls;

a plurality of trailing edge discharge holes extending from said fluid chambers to said trailing edge; and

a metering hole associated with each of said fluid chambers, each said metering hole defining a flow restriction connecting said cooling fluid channel to a respective fluid chamber.

2. The airfoil as set out in claim 1, wherein said plurality of fluid chambers are arranged in two spanwise rows comprising first ones of said fluid chambers defining a pressure side row located adjacent to said pressure sidewall, and second ones of said fluid chambers different from said first ones of said fluid chambers and defining a suction side row located adjacent to said suction sidewall.

3. The airfoil as set out in claim 2, wherein said trailing edge rib defines a rib centerline extending in a chordal direction between said pressure sidewall and said suction sidewall, and said pressure side row of said fluid chambers each defining a centerline offset from the rib centerline toward said pressure sidewall and said suction side row of said fluid chambers each defining a centerline offset from the rib centerline toward said suction sidewall.

4. The airfoil as set out in claim 2, wherein said fluid chambers of said pressure side row are located at spanwise locations that are aligned with spanwise locations of said fluid chambers of said suction side row.

5. The airfoil as set out in claim 2, wherein said fluid chambers of said pressure side row are located at spanwise locations that are offset relative to spanwise locations of said fluid chambers of said suction side row.

6. The airfoil as set out in claim 1, wherein each of said fluid chambers are formed as a conical segment having a larger chamber base section adjacent said cooling fluid channel and a smaller chamber tip section adjacent said trailing edge.

7. The airfoil as set out in claim 6, wherein each said fluid chamber includes a flat side located adjacent and substantially parallel to one of said pressure sidewall or said suction sidewall.

8. The airfoil as set out in claim 6, wherein each of said metering holes has a cross-sectional area that is smaller than a cross-sectional area of a respective chamber base section.

9. The airfoil as set out in claim 1, wherein said metering holes comprise different cross-sectional areas for different respective ones of said fluid compartments.

10. The airfoil as set out in claim 9, wherein said different cross-sectional areas of said metering holes are sized to correspond to variations in gas pressure profiles spanwise along said pressure sidewall and said suction sidewall adjacent to said trailing edge.

11. The airfoil as set out in claim 1, wherein each of said fluid chambers comprises a semi-circular cross-sectional profile.

12. A gas turbine engine hollow turbine airfoil comprising:

an outer wall surrounding a hollow interior;

said outer wall extending radially outwardly in a spanwise direction from an airfoil platform to an airfoil tip and having chordwise spaced apart leading and trailing edges, and widthwise spaced apart pressure and suction sidewalls extending chordwise between said leading edge and said trailing edge;

a trailing edge rib extending from said trailing edge toward said leading edge, said trailing edge rib forming a solid member between said pressure and suction sidewalls;

a cooling fluid channel extending in the spanwise direction through said airfoil adjacent to said trailing edge rib;

a first set of fluid chambers defining a plurality of pressure side fluid chambers formed in said trailing edge rib and extending chordwise between said cooling fluid channel and said trailing edge adjacent to said pressure sidewall;

a second set of fluid chambers defining a plurality of suction side fluid chambers formed in said trailing edge rib and extending chordwise between said cooling fluid channel and said trailing edge adjacent to said suction sidewall;

a plurality of film cooling holes extending from said pressure side fluid chambers to said pressure sidewall, and a plurality of film cooling holes extending from said suction side fluid chambers to said suction sidewall;

a trailing edge discharge hole extending from each of said fluid chambers to said trailing edge; and

a metering hole associated with each of said fluid chambers, each said metering hole defining a flow restriction connecting said cooling fluid channel to a respective fluid chamber.

13. The airfoil as set out in claim 12, wherein said pressure fluid chambers do not include film cooling holes extending to said suction sidewall, and said suction side fluid chambers do not include film cooling holes extending to said pressure sidewall.

14. The airfoil as set out in claim 12, wherein each of said fluid chambers are formed as a converging section having a decreasing cross-sectional area in a chordwise direction from said cooling fluid channel toward said trailing edge.

15. The airfoil as set out in claim 14, wherein said converging section comprises a conical segment having a larger chamber base section adjacent said cooling fluid channel and a smaller chamber tip section adjacent said trailing edge.

16. The airfoil as set out in claim 15, wherein each said pressure side fluid chamber includes a flat side located adjacent said pressure sidewall and each said suction side fluid chamber includes a flat side located adjacent said suction sidewall.

17. The airfoil as set out in claim 16, wherein each of said fluid chambers comprises a semi-circular cross-sectional profile.

18. The airfoil as set out in claim 14, wherein each of said metering holes has a cross-sectional area smaller than the cross-sectional area of a respective fluid chamber at an end adjacent to the cooling fluid channel.

19. The airfoil as set out in claim 12, wherein said metering holes comprise different cross-sectional areas for different respective ones of said fluid chambers.

20. The airfoil as set out in claim 19, wherein said different cross-sectional areas of said metering holes are sized to correspond to variations in gas pressure profiles spanwise along said pressure sidewall and said suction sidewall adjacent to said trailing edge.