High effectiveness cooled turbine vane or blade

• US 6,974,308 B2
• Filed: 11/14/2001
• Issued: 12/13/2005
• Est. Priority Date: 11/14/2001
• Status: Active Grant

• Current Assignee: Honeywell International Inc.
• Original Assignee: Honeywell International Inc.
• Inventors: Pack, David R., Morris, Mark C., Halfmann, Steve H., Wilson, Craig A., Ortiz, Milton, Kim, Yong W.
• Primary Examiner(s): VERDIER, CHRISTOPHER M
• Application Number:
  US09/992,250
• Publication Number:
  US 20040076519A1
• Time in Patent Office: 1,490 Days
• Field of Search: 415/115, 415/116, 416/96.R, 416/96.A, 416/97.R
• US Class Current: 416/97.00R
• CPC Class Codes: B22C 9/04 Use of lost patterns
• CPC Class Codes: B22C 9/103 Multipart cores
• CPC Class Codes: F01D 5/187 Convection cooling
• CPC Class Codes: F05D 2230/21 by casting
• CPC Class Codes: F05D 2260/202 by film cooling
• CPC Class Codes: F05D 2260/22141 using fins or ribs
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A robust multiple-walled, multi-pass, high cooling effectiveness cooled turbine vane or blade designed for ease of manufacturability, minimizes cooling flows on highly loaded turbine rotors. The vane or blade design allows the turbine inlet temperature to increase over current technology levels while simultaneously reducing turbine cooling to low levels. A multi-wall cooling system is described, which meets the inherent conflict to maximize the flow area of the cooling passages while retaining the required section thickness to meet the structural requirements. Independent cooling circuits for the vane or blade'"'"'s pressure and suction surfaces allow the cooling of the airfoil surfaces to be tailored to specific heat load distributions (that is, the pressure surface circuit is an independent forward flowing serpentine while the suction surface is an independent rearward flowing serpentine). The cooling air for the independent circuits is supplied through separate passages at the base of the vane or blade. The cooling air follows intricate passages to feed the serpentine thin outer wall passages, which incorporate pin fins, turbulators, etc. These passages, while satisfying the aero/thermal/stress requirements, are of a manufacturing configuration that may be cast with single crystal materials using conventional casting techniques.

Claims

1. An air-cooled turbine blade, the blade having an airfoil shape defined by a convex suction side wall, a concave pressure side wall, a leading edge, a trailing edge, a root and a tip, the walls, edges, root and tip forming an interior for receiving blade cooling circuits;

the turbine blade comprising;

a plurality of independent cooling circuits within said interior, one of said cooling circuits being positioned to cool said pressure side wall and one other of said cooling circuits being positioned to cool said suction side wall;

wherein said pressure side wall cooling circuit comprises a serpentine passage having a plurality of pin fins and a turning vane;

wherein said plurality of cooling circuits comprises two of said cooling circuits positioned to cool said suction side wall, one closer to said leading edge and one closer to said trailing edge; and

wherein said suction side wall cooling circuit closer to said trailing edge comprises a serpentine portion and a pin bank portion, said pin bank portion having a plurality of tear drop slots forming trailing edge air flow dividers for cooling said trailing edge.

2. The turbine blade recited in claim 1 wherein said plurality of cooling circuits comprises respective individual air inlets.

3. The turbine blade recited in claim 1 wherein said plurality of cooling circuits are mechanically interconnected to one another.

4. The turbine blade recited in claim 1 wherein said plurality of cooling circuits comprises two of said cooling circuits positioned to cool said suction side wall, one closer to the leading edge and one closer to the trailing edge.

5. The turbine blade recited in claim 1 wherein said plurality of cooling circuits comprises a cooling circuit positioned substantially in the center of said interior.

6. The turbine blade recited in claim 1 wherein said suction side cooling circuit closer to the leading edge comprises a plenum positioned adjacent said tip for cooling said tip.

7. The turbine blade recited in claim 1 wherein said pin bank portion comprises a plurality of pin fins, said tear drop slots having two said pin fins between adjacent slots.

8. The turbine blade recited in claim 1 wherein said pin bank portion comprises a trailing edge tip flag having tip strip turbulators positioned adjacent said blade tip.

9. The turbine blade recited in claim 1 wherein said pressure side wall cooling circuit comprises a super charger channel bypassing said serpentine passage.

10. An air-cooled turbine blade, the blade having an airfoil shape defined by a convex suction side wall, a concave pressure side wall, a leading edge, a trailing edge, a root and a tip, the walls, edges, root and tip forming an interior for receiving blade cooling circuits;

the turbine blade comprising;

a plurality of independent cooling circuits within said interior, one of said cooling circuits being positioned to cool said pressure side wall and one other of said cooling circuits being positioned to cool said suction side wall;

wherein said plurality of cooling circuits are mechanically interconnected to one another; and

wherein two of said cooling circuits are positioned to cool said suction side wall, one closer to the leading edge and one closer to the trailing edge;

wherein one of said plurality of cooling circuits is positioned substantially in the center of said interior; and

wherein said suction side wall cooling circuit closer to said trailing edge comprises a serpentine portion and a pin bank portion, said pin bank portion having a plurality of tear drop slots forming trailing edge air flow dividers for cooling said trailing edge.

11. The turbine blade recited in claim 10 wherein said cooling circuit positioned substantially at the center of said interior comprises walls having a greater thickness than the walls of said pressure side and suction side cooling circuits.

12. The turbine blade recited in claim 10 wherein said pressure side wall cooling circuit comprises a serpentine passage having a plurality of pin fins and a turning vane.

13. The turbine blade recited in claim 12 wherein said pressure side wall cooling circuit comprises a super charger channel bypassing said serpentine passage.

14. The turbine blade recited in claim 10 wherein said suction side cooling circuit closer to the leading edge comprises a plenum positioned adjacent said tip for cooling said tip.

15. The turbine blade recited in claim 10 wherein said pin bank portion comprises a plurality of pin fins, said tear drop slots having two said pin fins between adjacent slots.

16. The turbine blade recited in claim 10 wherein said pin bank portion comprises a trailing edge tip flag having tip strip turbulators positioned adjacent said blade tip.

17. An air-cooled turbine blade, the blade having an airfoil shape defined by a convex suction side wall, a concave pressure side wall, a leading edge, a trailing edge, a root and a tip, the walls, edges, root and tip forming an interior for receiving blade cooling circuits;

the turbine blade comprising;

a plurality of independent cooling circuits within said interior, one of said cooling circuits being positioned to cool said pressure side wall and one other of said cooling circuits being positioned to cool said suction side wall;

wherein said plurality of cooling circuits are mechanically interconnected to one another; and

wherein two of said cooling circuits are positioned to cool said suction side wall, one closer to the leading edge and one closer to the trailing edge;

wherein one of said plurality of cooling circuits is positioned substantially in the center of said interior and has walls having a greater thickness than the walls of said pressure side and suction side cooling circuits;

said pressure side wall cooling circuit having a serpentine passage, said passage having a plurality of pin fins and a turning vane;

said suction side cooling circuit closer to the leading edge having a plenum positioned adjacent said tip for cooling said tip;

said suction side wall cooling circuit closer to said trailing edge having a serpentine portion and a pin bank portion, said pin bank portion having a plurality of tear drop slots forming trailing edge air flow dividers for cooling said trailing edge.

18. The turbine blade recited in claim 17 wherein said pin bank comprises a plurality of pin fins, said tear drop slots having two said pin fins between adjacent slots.

19. The turbine blade recited in claim 17 wherein said pin bank portion comprises a trailing edge tip flag having tip strip tubulators positioned adjacent said blade tip.

20. The turbine blade recited in claim 17 wherein said pressure side wall cooling circuit comprises a super charger channel bypassing said serpentine passage.

21. A method for improving the cooling effectiveness of an air-cooled turbine blade, the blade having an airfoil shape defined by a convex suction side wall, a concave pressure side wall, a leading edge, a trailing edge, a root and a tip, the walls, edges, root and tip forming an interior for receiving blade cooling circuits;

the method comprising the steps of;

providing a plurality of independent cooling circuits within said interior;

positioning one of said cooling circuits substantially in the center of the interior;

providing said center-positioned cooling circuit with thicker walls than the walls of the remaining cooling circuits;

injecting cooling air into each said cooling circuit through respective independent air inlets;

positioning one of said cooling circuits adjacent said leading edge;

forming said leading edge adjacent said cooling circuit to have a plenum positioned for cooling said tip; and

reusing cooling air after it cools said plenum.

22. The method recited in claim 21 further comprising the steps of:

positioning one of said cooling circuits adjacent said suction side wall; and

positioning one of said cooling circuits adjacent said pressure sidewall.

23. The method recited in claim 22 further comprising the step of:

forming said pressure side adjacent cooling circuit with a serpentine passage having a plurality of pins and turning vane.

24. The method recited in claim 23 further comprising the step of optimizing the configuration of said plurality of pins to maximize heat transfer and optimizing the configuration of said turning vane to minimize flow separation.

25. The method recited in claim 22 further comprising the step of forming said suction side adjacent said cooling circuit to have an out of plane serpentine bend.

26. An air-cooled turbine blade, the blade having an airfoil shape defined by a convex suction side wall, a concave pressure side wall, a leading edge, a trailing edge, a root and a tip, with the walls, edges, root and tip forming an interior for receiving blade cooling circuits;

the turbine blade comprising;

a plurality of independent cooling circuits within said interior, a first of said cooling circuits being positioned to cool said pressure side wall, a second of said cooling circuits being positioned to cool said suction side wall, and a third of said cooling circuits positioned substantially in the center of said interior;

wherein said cooling circuit positioned substantially at the center of said interior comprises walls having a greater thickness than the walls of said pressure side and suction side cooling circuits;

wherein said plurality of cooling circuits comprises two of said cooling circuits positioned to cool said suction side wall, one closer to said leading edge and one closer to said trailing edge; and

wherein said suction side wall cooling circuit closer to said trailing edge comprises a serpentine portion and a pin bank portion, said pin bank portion having a plurality of tear drop slots forming trailing edge air flow dividers for cooling said trailing edge.

27. The turbine blade recited in claim 26 wherin said plurality of cooling circuits comprises respective individual air inlets.

28. The turbine blade recited in claim 26 wherein said plurality of cooling circuits are mechanically interconnected to one another.

29. The turbine blade recited in claim 26 wherein said pressure side wall cooling circuit comprises a serpentine passage having a plurality of pin fins and one turning vane.

30. The turbine blade recited in claim 29 wherein said pressure side wall cooling circuit comprises a super charger channel bypassing said serpentine passage.

31. The turbine blade recited in claim 26 wherein said suction side cooling circuit closer to the leading edge comprises a plenum positioned adjacent said tip for cooling said tip.

32. The turbine blade recited in claim 26 wherein said pin bank portion comprises a plurality of pin fins, said tear drop slots having two said pin fins between adjacent slots.

33. The turbine blade recited in claim 26 wherein said pin bank portion comprises a trailing edge tip flag having tip strip turbulators positioned adjacent said blade tip.

34. A method for improving the cooling effectiveness of an air-cooled turbine blade, the blade having an airfoil shape defined by a convex suction side wall, a concave pressure side wall, a leading edge, a trailing edge, a root and a tip, the walls, edges, root and tip forming an interior for receiving blade cooling circuits;

the method comprising the steps of;

providing a plurality of independent cooling circuits within said interior;

wherein one of said cooling circuits comprises a serpentine passage having a plurality of pins and a turning vane; and

injecting cooling air into each said cooling circuit through respective independent air inlets;

positioning one of said cooling circuits adjacent said leading edge;

forming said leading edge adjacent said cooling circuit to have a plenum positioned for cooling said tip; and

reusing cooling air after it cools said plenum.

35. The method recited in claim 34 further comprising the steps of:

positioning one of said cooling circuits adjacent said suction side wall; and

positioning one of said cooling circuits adjacent said pressure side wall.

36. The method recited in claim 35 further comprising the step of:

forming said pressure side adjacent cooling circuit with a serpentine passage having a plurality of pins and a turning vane.

37. The method recited in claim 35 further comprising the step of forming said suction side adjacent cooling circuit to have an out of plane serpentine bend.

38. The method recited in claim 34 further comprising the step of:

positioning one of said cooling circuits substantially in the center of said interior.

39. The turbine blade recited in claim 34 wherein said pressure side wall cooling circuit comprises a super charger channel bypassing said serpentine passage.