Turbine airfoil with integrated impingement and serpentine cooling circuit

• US 7,377,747 B2
• Filed: 06/06/2005
• Issued: 05/27/2008
• Est. Priority Date: 06/06/2005
• Status: Active Grant

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Lee, Ching-Pang
• Primary Examiner(s): Look; Edward K.
• Assistant Examiner(s): White; Dwayne J
• Application Number:
  US11/160,022
• Publication Number:
  US 20060275118A1
• Time in Patent Office: 1,086 Days
• Field of Search: 416/97.R, 416/96.R, 416/97.A, 416/90.R
• US Class Current: 416/97.00R
• 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 5/20 Specially-shaped blade tips to seal space between tips and stator F01D5/225 takes precedence
• CPC Class Codes: F01D 5/3007 of axial insertion type
• CPC Class Codes: F05D 2250/185 serpentine-like
• CPC Class Codes: F05D 2260/201 by impingement of a fluid
• 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
• CPC Class Codes: F05D 2260/607 Preventing clogging or obstruction of flow paths by dirt, dust, or foreign particles

Abstract

An airfoil for a gas turbine engine includes a generally radially-extending first cooling channel disposed between pressure and suction sidewalls adjacent the leading edge of the airfoil, and a generally radially-extending second cooling channel disposed aft of the first cooling channel. The second cooling channel is closed off at an outer end thereof and is disposed in fluid communication with a forward inlet an inner end thereof. The first and second cooling channels are separated by a partition having a plurality of impingement holes therein. A generally axially extending end channel is disposed radially outward from the second cooling channel in fluid communication with the first cooling channel and with a dust hole disposed in the tip cap. The dust hole is sized to permit the exit of debris entrained in a flow of cooling air from the airfoil.

Claims

1. An airfoil for a gas turbine engine having a longitudinal axis, said airfoil including a root, a tip, a leading edge, a trailing edge, and opposed pressure and suction sidewalls, and comprising:

a generally radially-extending first cooling channel disposed between said pressure and suction sidewalls adjacent said leading edge;

a generally radially-extending second cooling channel disposed aft of said first cooling channel, said second cooling channel being closed off at an outer end thereof and disposed in fluid communication with a forward inlet an inner end thereof;

a generally radially extending partition having a plurality of impingement holes disposed between said first and second cooling channels; and

a generally axially extending end channel disposed radially outward from said second cooling channel in fluid communication with said first cooling channel and with a first dust hole disposed in said tip cap, said first dust hole sized to permit the exit of debris entrained in a flow of cooling air from said airfoil.

2. The airfoil of claim 1 further comprising a plurality of generally radially-extending additional cooling channels disposed in said interior cavity and arranged to form an alternating inward and outward flowing serpentine flowpath.

3. The airfoil of claim 2 wherein:

one of said additional cooling channels is disposed adjacent said trailing edge to define a trailing edge cooling channel; and

a second dust hole is disposed in said tip cap in fluid communication with said trailing edge cooling channel.

4. The airfoil of claim 1 further comprising a plurality of elongated raised turbulators disposed in at least one of said cooling channels along at least one of said pressure and suction sidewalls, said turbulators oriented at an angle to a longitudinal axis of said airfoil.

5. The airfoil of claim 4 wherein said turbulators are disposed at an angle of about 30 to about 60 degrees to said longitudinal axis.

6. The airfoil of claim 1 further comprising a plurality of pins disposed in at least one of said cooling channels and extending between said pressure and suction sidewalls.

7. The airfoil of claim 1 further comprising at least one film cooling hole disposed in said pressure sidewall in flow communication with said interior cavity.

8. The airfoil of claim 1 further including at least one additional inlet extending between said root and said interior cavity.

9. The airfoil of claim 8 wherein:

one of said additional cooling channels is disposed adjacent said trailing edge to define a trailing edge cooling channel; and

said additional inlet is disposed in fluid communication with said trailing edge cavity.

10. The airfoil of claim 1 wherein said dust hole is about 0.64 mm or greater in diameter.

11. A turbine blade for a gas turbine engine, comprising:

a dovetail adapted to be received in a disk rotatable about a longitudinal axis;

a laterally-extending platform disposed radially outwardly from said dovetail; and

an airfoil including a root, a tip, a leading edge, a trailing edge, and opposed pressure and suction sidewalls, said airfoil comprising;

a generally radially-extending first cooling channel disposed between said pressure and suction sidewalls adjacent said leading edge;

a generally radially-extending second cooling channel disposed aft of said first cooling channel, said second cooling channel being closed off at an outer end thereof and disposed in fluid communication with a forward inlet an inner end thereof;

a generally radially extending partition having a plurality of impingement holes disposed between said first and second cooling channels; and

a generally axially extending end channel disposed radially outward from said second cooling channel in fluid communication with said first cooling channel and with a first dust hole disposed in said tip cap, said first dust hole sized to permit the exit of debris entrained in a flow of cooling air from said airfoil.

12. The turbine blade of claim 11 further comprising a plurality of generally radially-extending additional cooling channels disposed in said interior cavity and arranged to form an alternating inward and outward flowing serpentine flowpath.

13. The turbine blade of claim 12 wherein:

one of said additional cooling channels is disposed adjacent said trailing edge to define a trailing edge cooling channel; and

a second dust hole is disposed in said tip cap in fluid communication with said trailing edge cooling channel.

14. The turbine blade of claim 11 further comprising a plurality of elongated raised turbulators disposed in at least one of said cooling channels along at least one of said pressure and suction sidewalls, said turbulators oriented at an angle to a longitudinal axis of said airfoil.

15. The turbine blade of claim 14 wherein said turbulators are disposed at an angle of about 30 degrees to about 60 degrees to said longitudinal axis.

16. The turbine blade of claim 11 further comprising a plurality of pins disposed in at least one of said cooling channels and extending between said pressure and suction sidewalls.

17. The turbine blade of claim 11 further comprising at least one film cooling hole disposed in said pressure sidewall in flow communication with said interior cavity.

18. The turbine blade of claim 11 further including at least one additional inlet extending between said dovetail and said interior cavity.

19. The turbine blade of claim 18 wherein:

one of said additional cooling channels is disposed adjacent said trailing edge to define a trailing edge cooling channel; and

said additional inlet is disposed in fluid communication with said trailing edge cavity.

20. The turbine blade of claim 11 wherein said dust hole is about 0.64 mm or greater in diameter.