Turbine airfoil trailing edge cooling slots

• US 9,175,569 B2
• Filed: 03/30/2012
• Issued: 11/03/2015
• Est. Priority Date: 03/30/2012
• Status: Active Grant

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Bergholz, Robert Frederick Jr., Durstock, Daniel Lee
• Primary Examiner(s): White, Dwayne J
• Assistant Examiner(s): GRIGOS, WILLIAM G
• Application Number:
  US13/435,302
• Publication Number:
  US 20130259645A1
• Time in Patent Office: 1,313 Days
• Field of Search: 415/115, 416/96.R, 416/96.A, 416/97.R, 416/97.A
• US Class Current: 1/1
• CPC Class Codes: F01D 5/18 Hollow blades, i.e. blades with cooling or heating channels or cavities structure of hollow blades in general F01D5/147; Heating, heat-insulating or cooling means on blades
• CPC Class Codes: F01D 5/186 Film cooling F01D5/187 takes precedence
• CPC Class Codes: F01D 5/187 Convection cooling
• CPC Class Codes: F01D 9/02 Nozzles; Nozzle boxes; Stator blades; Guide conduits , e.g. individual nozzles nozzle boxes F01D9/047
• CPC Class Codes: F05D 2240/304 related to the trailing edge of a rotor blade
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A turbine airfoil includes pressure and suction sidewalls extending along a span from a base to a tip. Spanwise spaced apart trailing edge cooling holes in the pressure sidewall end at corresponding spanwise spaced apart trailing edge cooling slots extending chordally substantially to the trailing edge. Each cooling hole includes in downstream serial cooling flow relationship, a curved inlet, a constant area and constant width metering section, and a spanwise diverging section leading into the trailing edge cooling slot, and a spanwise height substantially greater than a hole width through the cooling hole. A pressure sidewall surface of the pressure sidewall may be planar through the metering and diverging sections. The width may be constant through the metering and diverging sections. A raised floor may include a flat up ramp in the diverging section, a flat down ramp in the slot.

Claims

1. A gas turbine engine turbine airfoil comprising:

widthwise spaced apart pressure and suction sidewalls extending outwardly along a span from an airfoil base to an airfoil tip;

the pressure and suction sidewalls extending chordwise between opposite leading and trailing edges;

a spanwise row of spanwise spaced apart trailing edge cooling holes encased in the pressure sidewall and ending at corresponding spanwise spaced apart trailing edge cooling slots extending chordally substantially to the trailing edge;

the cooling hole including in downstream serial cooling flow relationship, a curved inlet, a metering section with a constant area and constant width flow cross section, and a spanwise diverging section leading into the trailing edge cooling slot; and

a spanwise height substantially greater than a hole width through the cooling hole;

at least one of the cooling holes including a raised floor extending downstream through each of the diverging sections starting at the end of the corresponding metering section and into and at least partially through the corresponding cooling slot;

the raised floor including in downstream serial relationship a flat up ramp in the diverging section, a flat down ramp in the trailing edge cooling slot, and a transition section between the up and down ramps;

the up ramp ramping up and extending downstream from the suction sidewall surface at the end of the metering section; and

the down ramp ramping down and extending downstream from the transition section to the trailing edge.

2. The airfoil as claimed in claim 1 further comprising pressure and suction sidewall surfaces of the pressure and suction sidewalls respectively in the hole and the pressure sidewall surface being planar through the entire metering and diverging sections.

3. The airfoil as claimed in claim 2 further comprising the width being constant through the metering and diverging sections of the hole.

4. The airfoil as claimed in claim 3 further comprising lands disposed between spanwise adjacent ones of the trailing edge cooling slots and slot floors in the trailing edge cooling slots between the lands.

5. The airfoil as claimed in claim 4 further comprising the lands being coplanar or flush with an external surface of the pressure sidewall around each of the cooling slots.

6. The airfoil as claimed in claim 4 further comprising:

the diverging section having a race track shaped flow cross section,

the race track shaped flow cross section including a rectangular section between spanwise spaced apart rounded or semi-circular inner and outer end sections,

the race track shaped flow cross section including a rectangular section between spanwise spaced apart rounded or semi-circular inner and outer end sections having corner radii,

fillets in slot corners between the lands and the slot floors, and

the fillets having fillet radii substantially the same size as the corner radii of the flow cross section.

7. The airfoil as claimed in claim 4 further comprising the diverging section and the trailing edge cooling slot diverging at different first and second diverging angles respectively.

8. The airfoil as claimed in claim 7 further comprising the lands being coplanar or flush with an external surface of the pressure sidewall around each of the cooling slots.

9. The airfoil as claimed in claim 7 further comprising:

the diverging section having a race track shaped flow cross section,

the race track shaped flow cross section including a rectangular section between spanwise spaced apart rounded or semi-circular inner and outer end sections having corner radii,

fillets in slot corners between the lands and the slot floors, and

the fillets having fillet radii substantially the same size as the corner radii of the flow cross section.

10. The airfoil as claimed in claim 1 further comprising the metering and diverging sections having a hole height to hole width ratio of the spanwise height and the hole width in a range of about 2:

1 to 10;

1.

11. The airfoil as claimed in claim 10 further comprising pressure and suction sidewall surfaces of the pressure and suction sidewalls respectively in the hole and the pressure sidewall surface being planar through the entire metering and diverging sections.

12. The airfoil as claimed in claim 11 further comprising the width being constant through the metering and diverging sections of the hole.

13. The airfoil as claimed in claim 12 further comprising lands disposed between spanwise adjacent ones of the trailing edge cooling slots and slot floors in the trailing edge cooling slots between the lands.

14. The airfoil as claimed in claim 13 further comprising the lands being coplanar or flush with an external surface of the pressure sidewall around each of the cooling slots.

15. The airfoil as claimed in claim 13 further comprising:

the diverging section having a race track shaped flow cross section,

the race track shaped flow cross section including a rectangular section between spanwise spaced apart rounded or semi-circular inner and outer end sections having corner radii,

fillets in slot corners between the lands and the slot floors, and

the fillets having fillet radii substantially the same size as the corner radii of the flow cross section.

16. The airfoil as claimed in claim 13 further comprising the diverging section and the trailing edge cooling slot diverging at different first and second diverging angles respectively.

17. The airfoil as claimed in claim 16 further comprising the lands being coplanar or flush with an external surface of the pressure sidewall around each of the cooling slots.

18. The airfoil as claimed in claim 16 further comprising:

the diverging section having a race track shaped flow cross section,

the race track shaped flow cross section including a rectangular section between spanwise spaced apart rounded or semi-circular inner and outer end sections having corner radii,

fillets in slot corners between the lands and the slot floors, and

the fillets having fillet radii substantially the same size as the corner radii of the flow cross section.

19. The airfoil as claimed in claim 13 further comprising the inlet being downstream converging or bellmouth shaped.

20. The airfoil as claimed in claim 19 further comprising the lands being coplanar or flush with an external surface of the pressure sidewall around each of the cooling slots.

21. The airfoil as claimed in claim 19 further comprising:

the diverging section having a race track shaped flow cross section,

the race track shaped flow cross section including a rectangular section between spanwise spaced apart rounded or semi-circular inner and outer end sections,

the inner and outer end sections including corner radii,

fillets in slot corners between the lands and the slot floors, and

the fillet radii being substantially the same size as the corner radii of the flow cross section.

22. The airfoil as claimed in claim 19 further comprising the diverging section and the trailing edge cooling slot diverging at different first and second diverging angles respectively.

23. The airfoil as claimed in claim 22 further comprising the lands being coplanar or flush with an external surface of the pressure sidewall around each of the cooling slots.

24. The airfoil as claimed in claim 22 further comprising:

the diverging section having a race track shaped flow cross section,

the race track shaped flow cross section including a rectangular section between spanwise spaced apart rounded or semi-circular inner and outer end sections,

the inner and outer end sections including corner radii,

fillets in slot corners between the lands and the slot floors, and

the fillet radii being substantially the same size as the corner radii of the flow cross section.

25. The airfoil as claimed in claim 1 further comprising lands disposed between spanwise adjacent ones of the trailing edge cooling slots and slot floors in the trailing edge cooling slots between the lands.

26. The airfoil as claimed in claim 25 further comprising the lands being coplanar or flush with an external surface of the pressure sidewall around each of the cooling slots.

27. The airfoil as claimed in claim 25 further comprising:

the diverging section having a race track shaped flow cross section,

the race track shaped flow cross section including a rectangular section between spanwise spaced apart rounded or semi-circular inner and outer end sections,

the inner and outer end sections including corner radii,

fillets in slot corners between the lands and the slot floors, and

the fillet radii being substantially the same size as the corner radii of the flow cross section.

28. The airfoil as claimed in claim 25 further comprising the diverging section and the trailing edge cooling slot diverging at different first and second diverging angles respectively.

29. The airfoil as claimed in claim 28 further comprising:

the diverging section having a race track shaped flow cross section,

the race track shaped flow cross section including a rectangular section between spanwise spaced apart rounded or semi-circular inner and outer end sections,

the inner and outer end sections including corner radii,

fillets in slot corners between the lands and the slot floors, and

the fillet radii being substantially the same size as the corner radii of the flow cross section.

30. The airfoil as claimed in claim 1 further comprising the metering and diverging sections having a hole height to hole width ratio of the spanwise height and the hole width in a range of about 2:

1 to 10;

1.

31. The airfoil as claimed in claim 30 further comprising pressure and suction sidewall surfaces of the pressure and suction sidewalls respectively in the hole and the pressure sidewall surface being planar through the entire metering and diverging sections.

32. The airfoil as claimed in claim 31 further comprising lands disposed between spanwise adjacent ones of the trailing edge cooling slots and slot floors in the trailing edge cooling slots between the lands.

33. The airfoil as claimed in claim 32 further comprising the diverging section and the trailing edge cooling slot diverging at different first and second diverging angles respectively.

34. The airfoil as claimed in claim 33 further comprising the inlet being downstream converging or bellmouth shaped.

35. The airfoil as claimed in claim 4 further comprising the lands angled towards the slot floor and away from an external surface of the pressure sidewall and the lands intercepting the slot floor upstream of the trailing edge.

36. The airfoil as claimed in claim 35 further comprising the lands angled away from the external surface by a land angle in a range between 0-5 degrees.

37. The airfoil as claimed in claim 36 further comprising the diverging section and the trailing edge cooling slot diverging at different first and second diverging angles respectively.

38. The airfoil as claimed in claim 35 further comprising:

the diverging section having a race track shaped flow cross section,

the race track shaped flow cross section including a rectangular section between spanwise spaced apart rounded or semi-circular inner and outer end sections having corner radii,

fillets in slot corners between the lands and the slot floors, and

the fillets having fillet radii substantially the same size as the corner radii of the flow cross section.

39. The airfoil as claimed in claim 35 further comprising the metering and diverging sections having a hole height to hole width ratio of the spanwise height and the hole width in a range of about 2:

1 to 10;

1.

40. The airfoil as claimed in claim 34 further comprising pressure and suction sidewall surfaces of the pressure and suction sidewalls respectively in the hole and the pressure sidewall surface being planar through the entire metering and diverging sections.

41. The airfoil as claimed in claim 40 further comprising the width being constant through the metering and diverging sections of the hole.