Inboard cooled nozzle doublet

• US 20050135921A1
• Filed: 12/17/2003
• Published: 06/23/2005
• Est. Priority Date: 12/17/2003
• Status: Active Grant

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Powis, Andrew Charles, Busch, Duane Allan, Starkweather, Melissa Wise
• Granted Patent: US 7,008,178 B2
• Time in Patent Office: Days
• US Class Current: 415/115
• CPC Class Codes: C23C 14/541 Heating or cooling of the substrates
• CPC Class Codes: F01D 5/189 the insert having a tubular cross-section, e.g. airfoil shape
• CPC Class Codes: F01D 5/288 Protective coatings for blades
• CPC Class Codes: F05D 2230/313 by physical vapour deposition
• CPC Class Codes: F05D 2230/314 by chemical vapour deposition
• CPC Class Codes: F05D 2230/90 Coating; Surface treatment manufacture with deposition of material F05D2230/30
• CPC Class Codes: F05D 2260/201 by impingement of a fluid
• CPC Class Codes: F05D 2260/202 by film cooling
• CPC Class Codes: F05D 2300/611 Coating
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A turbine nozzle includes outer and inner bands integrally joined to a doublet of hollow vanes extending radially therebetween. Each of the vanes includes opposite pressure and suction sidewalls extending between opposite leading and trailing edges, and spaced apart to define an internal plenum extending radially between the bands for receiving an air coolant. The vanes are spaced apart from each other to define a flow passage for channeling hot combustion gases which are bound by corresponding pressure and suction sidewalls of the vanes facing inboard toward each other, with the remaining suction and pressure sidewalls of the vanes facing outboard. The vanes include different cooling configurations to bias more of the coolant to the inboard sidewalls than to the outboard sidewalls.

Claims

1. A turbine nozzle comprising:

radially outer and inner bands integrally joined to a doublet of hollow vanes extending radially in span therebetween;

each of said vanes including circumferentially opposite pressure and suction sidewalls extending axially between opposite leading and trailing edges, and spaced apart to define an internal plenum extending radially between said bands for receiving an air coolant therein;

said vanes being spaced apart from each other to define a flow passage therebetween for channeling hot combustion gases bound by corresponding pressure and suction sidewalls of said vanes facing inboard toward each other, with the remaining suction and pressure sidewalls of said vanes facing outboard; and

said doublet of vanes including different cooling configurations, to bias more of said coolant to said inboard sidewalls than to said outboard sidewalls.

2. A nozzle according to claim 1 wherein:

each of said vanes includes an impingement baffle disposed inside said plenum and aperture outlets extending through said sidewalls thereof; and

said baffles and outlets cooperate to effect said different cooling configurations.

3. A nozzle according to claim 2 wherein said baffles include different patterns of impingement cooling holes therein.

4. A nozzle according to claim 3 wherein said impingement hole patterns are configured to distribute more of said coolant to said inboard sidewalls than to said outboard sidewalls.

5. A nozzle according to claim 4 wherein:

said outboard sidewalls of said vanes are covered by a full thickness thermal barrier coating between said leading and trailing edges and wrapping around said leading edges; and

said inboard sidewalls of said vanes are covered by a partial thickness thermal barrier coating extending aft from said full thickness thermal barrier coating wrapping around said leading edges.

6. A nozzle according to claim 5 wherein:

said impingement hole patterns and vane outlets are configured to distribute more of said coolant against said inboard sidewalls corresponding with said partial thickness thermal barrier coating thereon than against said outboard sidewalls corresponding with said full thickness thermal barrier coating thereon; and

said impingement hole patterns are further configured to distribute more of said coolant against said inboard suction sidewall than against said inboard pressure sidewall.

7. A nozzle according to claim 6 wherein:

said outboard suction sidewall is imperforate;

said inboard suction sidewall includes a row of first outlets;

said outboard pressure sidewall includes a row of second outlets; and

said inboard pressure sidewall includes a row of third outlets.

8. A nozzle according to claim 7 wherein:

said inboard suction sidewall is imperforate between said leading and trailing edges except for a single row of said first outlets;

said second outlets extend through said outboard pressure sidewall aft of said plenum in said vane and forward of said trailing edge thereof; and

said third outlets extend through said inboard pressure sidewall aft of said plenum in said vane and forward of said trailing edge thereof.

9. A nozzle according to claim 8 wherein:

said vanes further include corresponding rows of trailing edge outlets terminating along said pressure sidewalls forward of said trailing edges in flow communication with said corresponding plenums in said vanes; and

said pressure sidewalls are imperforate except for said rows of second and third outlets trailing edge outlets.

10. A nozzle according to claim 9 wherein:

said first outlets comprise diffusion film cooling holes; and

said second and third outlets comprise inclined film cooling holes extending through said pressure sidewalls.

11. A turbine nozzle 16 comprising:

radially outer and inner bands integrally joined to a doublet of hollow vanes extending radially in span therebetween;

each of said vanes including circumferentially opposite pressure and suction sidewalls extending axially between opposite leading and trailing edges, and spaced apart to define an internal plenum extending radially between said bands for receiving an air coolant therein;

said vanes being spaced apart from each other to define a flow passage therebetween for channeling hot combustion gases bound by corresponding pressure and suction sidewalls of said vanes facing inboard toward each other, with the remaining suction and pressure sidewalls of said vanes facing outboard; and

means for biasing more of said coolant to said inboard sidewalls than to said outboard sidewalls.

12. A nozzle according to claim 11 wherein said doublet of vanes includes different cooling configurations to effect said coolant biasing between said inboard and outboard sidewalls.

13. A nozzle according to claim 12 wherein said different cooling configurations are sized to effect different flowrates of said coolant through said vane.

14. A nozzle according to claim 12 wherein each of said vanes includes aperture outlets through said sidewalls thereof to effect said different cooling configurations.

15. A nozzle according to claim 14 wherein said outboard suction sidewall is imperforate and said inboard suction sidewall includes a row of first outlets.

16. A nozzle according to claim 15 wherein said first outlets extend through said inboard suction sidewall at a forward end of said plenum in said vane and aft of said leading edge thereof.

17. A nozzle according to claim 16 wherein said inboard suction sidewall is imperforate forward to said leading edge and aft to said trailing edge from said first outlets therein.

18. A nozzle according to claim 17 wherein said first outlets comprise diffusion film cooling holes.

19. A nozzle according to claim 17 wherein:

said outboard suction sidewall is covered by a full thickness thermal barrier coating between said leading and trailing edges of said vane; and

said inboard suction sidewall is covered by a full thickness thermal barrier coating forward of said first outlets, and a partial thickness thermal barrier coating aft of said first outlets.

20. A nozzle according to claim 19 wherein said inboard suction sidewall is covered by a full thickness thermal barrier coating forward of said trailing edge of said vane that blends with said partial thickness thermal barrier coating extending toward said first outlets.

21. A nozzle according to claim 14 wherein said outboard and inboard pressure sidewalls include corresponding rows of second and third outlets having different configurations.

22. A nozzle according to claim 21 wherein:

said second outlets extend through said outboard pressure sidewall aft of said plenum in said vane and forward of said trailing edge thereof; and

said third outlets extend through said inboard pressure sidewall aft of said plenum in said vane and forward of said trailing edge thereof.

23. A nozzle according to claim 21 wherein said pressure sidewalls are imperforate forward of said corresponding second and third outlets to said corresponding leading edges.

24. A nozzle according to claim 23 wherein said vanes further include corresponding rows of trailing edge outlets disposed adjacent said trailing edges thereof in flow communication with said corresponding plenums therein.

25. A nozzle according to claim 24 wherein said pressure sidewalls are imperforate between said trailing edge outlets and said rows of second and third outlets.

26. A nozzle according to claim 24 wherein said second and third outlets comprise inclined film cooling holes extending through said pressure sidewalls.

27. A nozzle according to claim 24 wherein said trailing edge outlets comprise slots terminating along said pressure sidewalls forward of said trailing edges.

28. A nozzle according to claim 24 wherein:

said outboard pressure sidewall is covered by a full thickness thermal barrier coating between said leading and trailing edges of said vane and around said second outlets; and

said inboard pressure sidewall is covered by a partial thickness thermal barrier coating between said leading and trailing edges of said vane and around said third outlets.

29. A nozzle according to claim 28 wherein:

said full thickness thermal barrier coating surrounds said leading edges of said vanes, and extends aft along said outboard pressure sidewall short of said trailing edge outlets, and extends aft along said inboard pressure sidewall to blend with said partial thickness thermal barrier coating; and

said partial thickness thermal barrier coating extends aft along said inboard pressure sidewall short of said trailing edge outlets.

30. A nozzle according to claim 12 wherein:

each of said vanes includes an impingement baffle disposed inside said plenum; and

said baffles include different patterns of impingement cooling holes therein to effect said different cooling configurations.

31. A nozzle according to claim 30 wherein said impingement hole patterns are configured to distribute more of said coolant to said inboard sidewalls than to said outboard sidewalls.

32. A nozzle according to claim 31 wherein said baffle impingement holes have uniform size in both vanes, and differ in quantity to distribute more of said coolant in impingement against the internal surfaces of said inboard sidewalls.

33. A nozzle according to claim 32 wherein said impingement hole patterns in said baffles are different from each other along both said inboard sidewalls and along said outboard sidewalls.

34. A nozzle according to claim 30 wherein each of said baffles includes a floor spaced from said inner band, and said floor includes a dump outlet differently sized in said two baffles.

35. A nozzle according to claim 30 wherein:

said outer band includes corresponding seats through which said baffles are suspended in said vanes, each of said seats including a socket differently located above said vanes; and

each of said baffles includes a corresponding alignment pin extending differently outwardly from outer ends thereof and disposed in respective ones of said sockets.

36. A nozzle according to claim 35 wherein said alignment pins and sockets are disposed in said outer band in alignment with said outboard sidewalls.