Low cost airfoil cooling circuit with sidewall impingement cooling chambers

• US 6,206,638 B1
• Filed: 02/12/1999
• Issued: 03/27/2001
• Est. Priority Date: 02/12/1999
• Status: Expired due to Fees

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Wilson, Paul S., Carlson, Clay K., Glynn, Christopher C., Martus, James A.
• Primary Examiner(s): Look, Edward K.
• Assistant Examiner(s): WOO, RICHARD SUKYOON
• Application Number:
  US09/249,204
• Time in Patent Office: 774 Days
• Field of Search: 415/115, 416/97.R, 416/96.R, 416/96.A, 416/97.A
• US Class Current: 416/97.00R
• CPC Class Codes: F01D 5/186 Film cooling F01D5/187 takes precedence
• CPC Class Codes: F01D 5/187 Convection cooling
• CPC Class Codes: F05D 2230/21 by casting
• CPC Class Codes: F05D 2260/201 by impingement of a fluid
• CPC Class Codes: F05D 2260/202 by film cooling
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A gas turbine engine airfoil includes an airfoil outer wall having widthwise spaced apart pressure and suction sidewall sections extending chordally between leading and trailing edges of the airfoil and extending longitudinally from a base to a tip. Inside the airfoil is at least one internal cooling circuit having a plurality of longitudinally extending circuit channels between longitudinally extending internal ribs extending widthwise between the pressure and suction sidewall sections and a longitudinally extending first sidewall film cooling chamber positioned between one of the sidewall sections and a first inner wall bounding the cooling circuit. Sidewall film cooling holes extend through the pressure sidewall section from the first sidewall film cooling chamber. The internal ribs have corresponding rib angles with respect to a centerline, the first inner wall has a corresponding first wall angle with respect to the centerline, and each of the rib angles and the first wall angle are constant in a longitudinal direction from the base to the tip. In the preferred embodiment, all the inner walls are substantially parallel to each other and all the transverse ribs are substantially parallel to each other or are substantially parallel to the first and second inner walls.

Claims

1. A gas turbine engine airfoil circumscribed about an engine centerline, said airfoils comprising:

an airfoil outer wall having widthwise spaced apart pressure and suction sidewall sections extending chordally between leading and trailing edges of said airfoil and extending longitudinally from a base to a tip in a radially outwardly direction from said centerline;

at least one internal cooling circuit having a plurality of longitudinally extending circuit channels between longitudinally extending internal ribs extending widthwise between said pressure and suction sidewall sections;

a longitudinally extending first sidewall film cooling chamber positioned between one of said sidewall sections, a first one of said internal ribs, and a first inner wall bounding said cooling circuit and a first plurality of sidewall film cooling holes extend through said pressure sidewall section from said first sidewall film cooling chamber;

said internal ribs having corresponding rib angles with respect to said centerline,

said first inner wall having a corresponding first wall angle with respect to said centerline,

each of said rib angles and said first wall angle being constant in a longitudinal direction from said base to said tip, and

a plurality of first impingement cooling apertures extending from a first one of said circuit channels through said first one of said internal ribs to said first sidewall film cooling chamber.

2. An airfoil as claimed in claim 1 having two sets of said internal ribs wherein said internal ribs in a first set are substantially parallel to each other and said internal ribs in a second set are substantially parallel to said first inner wall.

3. An airfoil as claimed in claim 2 wherein said first sidewall film cooling chamber is triangular in cross-section.

4. An airfoil as claimed in claim 3 wherein said first impingement cooling apertures are located along an interior corner of said first sidewall film cooling chamber.

5. An airfoil as claimed in claim 4 wherein said one of said sidewall sections is said pressure sidewall section.

6. An airfoil as claimed in claim 5 wherein said internal cooling circuit is a serpentine cooling circuit.

7. An airfoil as claimed in claim 6 wherein said first sidewall film cooling chamber segmented into compartments with shelves extending cross-sectionally entirely across said first sidewall film cooling chamber between each of said compartments.

8. An airfoil as claimed in claim 3 wherein said first impingement cooling apertures are arranged in a staggered array in at least two longitudinally extending rows such that said first impingement cooling apertures are centered along a single zig-zag line.

9. An airfoil as claimed in claim 8 wherein said one of said sidewall sections is said pressure sidewall section and said internal cooling circuit is a serpentine cooling circuit.

10. An airfoil as claimed in claim 3 wherein said first sidewall film cooling chamber segmented into compartments with shelves extending cross-sectionally entirely across said first sidewall film cooling chamber between each of said compartments.

11. An airfoil as claimed in claim 2 wherein said internal cooling circuit is a serpentine cooling circuit.

12. An airfoil as claimed in claim 2 further comprising:

a longitudinally extending second sidewall film cooling chamber positioned between said one of said sidewall sections, a second one of said internal ribs, and a second inner wall bounding said cooling circuit,

said second inner wall having a corresponding second wall angle with respect to said centerline and said second wall angle being substantially constant in said longitudinal direction from said base to said tip,

a plurality of second impingement cooling apertures extending from a second one of said circuit channels through said second one of said internal ribs to said second sidewall film cooling chamber, and

said first and second inner walls being parallel to each other.

13. An airfoil as claimed in claim 12 wherein said first and second sidewall film cooling chambers are triangular in cross-section.

14. An airfoil as claimed in claim 13 wherein each of said first and second impingement pluralities of cooling apertures are arranged staggered arrays in at least two longitudinally extending rows such that said first impingement cooling apertures are centered along a single zig-zag line, said one of said sidewall sections is said pressure sidewall section and first and second pluralities of sidewall film cooling holes extend through said pressure sidewall section from said first and second sidewall film cooling chambers respectively, and said internal cooling circuit is a serpentine cooling circuit.

15. An airfoil as claimed in claim 14 wherein said first sidewall film cooling chamber segmented into compartments with shelves extending cross-sectionally entirely across said first sidewall film cooling chamber between each of said compartments.

16. An airfoil as claimed in claim 14 wherein said first and second impingement cooling apertures are located along interior corners of said first and second sidewall film cooling chambers.

17. An airfoil as claimed in claim 16 wherein said one of said sidewall sections is said pressure sidewall section and first and second pluralities of sidewall film cooling holes extend through said pressure sidewall section from said first and second sidewall film cooling chambers respectively.

18. An airfoil as claimed in claim 17 wherein said internal cooling circuit is a serpentine cooling circuit.

19. An airfoil as claimed in claim 16 further comprising:

leading edge and trailing edge cooling plenums along said leading and trailing edges,

said leading edge and trailing edge cooling plenums having cooling air discharge apertures in said outer wall along said leading edge and trailing edges respectively,

said leading edge cooling plenum having leading edge feed apertures through a leading edge span rib of a forward feed channel located forward of said internal serpentine cooling circuit,

a plurality of leading edge cooling apertures extend out of said leading edge cooling plenum through said outer wall around said leading edge,

said trailing edge cooling plenum having trailing edge feed apertures through a trailing edge span rib of an aft feed channel located aft of said internal serpentine cooling circuit,

a plurality of trailing edge cooling apertures extend out of said trailing edge cooling plenum through said outer wall at said trailing edge, and

said leading and trailing edge span ribs have corresponding span rib angles with respect to said centerline and each of said span rib angles is constant in a longitudinal direction from said base to said tip.

20. An airfoil as claimed in claim 19 further comprising:

an outer tip wall which caps said cooling circuit at said tip,

a squealer tip having a squealer wall extending longitudinally outward from and peripherally around said outer tip wall forming a squealer tip cavity therein,

at least one tip cooling hole extending out though said tip wall from each of said first and second sidewall film cooling chambers.

21. An airfoil as claimed in claim 1 further comprising:

two sets of said internal ribs wherein said internal ribs in a first set are substantially parallel to each other and said internal ribs in a second set are substantially parallel to said first inner wall,

said first sidewall film cooling chamber being triangular in cross-section, and

a metering inlet at a radially inner base of said airfoil for supplying all cooling air to said first sidewall film cooling chamber.

22. An airfoil as claimed in claim 1 further comprising:

a longitudinally extending second sidewall film cooling chamber positioned between said one of said sidewall sections and a second inner wall bounding said cooling circuit,

said second inner wall having a corresponding second wall angle with respect to said centerline and said second wall angle being substantially constant in said longitudinal direction from said base to said tip,

said first and second inner walls being parallel to each other,

two sets of said internal ribs wherein said internal ribs in a first set are substantially parallel to each other and said internal ribs in a second set are substantially parallel to said first and second inner walls,

said first and second sidewall film cooling chambers being triangular in cross-section, and

a metering inlet at a radially inner base of said airfoil for supplying all cooling air to said first and second sidewall film cooling chambers.

23. A gas turbine engine airfoil circumscribed about an engine centerline, said airfoil comprising:

an airfoil outer wall having widthwise spaced apart pressure and suction sidewall sections extending chordally between leading and trailing edges of said airfoil and extending longitudinally from a base to a tip in a radially outwardly direction from said centerline;

at least one internal cooling circuit having a plurality of longitudinally extending circuit channels between longitudinally extending internal ribs extending widthwise between said pressure and suction sidewall sections;

a longitudinally extending first sidewall film cooling chamber positioned between one of said sidewall sections, a first one of said internal ribs, and a first inner wall bounding said cooling circuit and a first plurality of sidewall film cooling holes extend through said pressure sidewall section from said first sidewall film cooling chamber;

said internal ribs having corresponding rib angles with respect to said centerline;

said first inner wall having a corresponding first wall angle with respect to said centerline;

each of said rib angles and said first wall angle being constant in a longitudinal direction from said base to said tip; and

each of said ribs being parallel to another one of said ribs or said first inner wall.

24. An airfoil as claimed in claim 23 further comprising a plurality of first impingement cooling apertures extending from at least a first one of said circuit channels through said first one of said internal ribs to said internal cooling circuit.

25. An airfoil as claimed in claim 24 having two sets of said internal ribs wherein said internal ribs in a first set are substantially parallel to each other and said internal ribs in a second set are substantially parallel to said first inner wall.

26. An airfoil as claimed in claim 25 further comprising:

a longitudinally extending second sidewall film cooling chamber positioned between said one of said sidewall sections, a second one of said internal ribs, and a second inner wall bounding said cooling circuit,

said second inner wall having a corresponding second wall angle with respect to said centerline and said second wall angle being substantially constant in said longitudinal direction from said base to said tip,

a plurality of second impingement cooling apertures extending from a second one of said circuit channels through said second one of said internal ribs to said second sidewall film cooling chamber, and

said first and second inner walls being parallel to each other.

27. An airfoil as claimed in claim 26 wherein said first and second sidewall film cooling chambers are triangular in cross-section.

28. An airfoil as claimed in claim 27 wherein said one of said sidewall sections is said pressure sidewall section and first and second pluralities of sidewall film cooling holes extend through said pressure sidewall section from said first and second sidewall film cooling chambers respectively.

29. An airfoil as claimed in claim 27 wherein each of said first and second impingement pluralities of cooling apertures are arranged staggered arrays in at least two longitudinally extending rows such that said first impingement cooling apertures are centered along a single zig-zag line, said one of said sidewall sections is said pressure sidewall section and first and second pluralities of sidewall film cooling holes extend through said pressure sidewall section from said first and second sidewall film cooling chambers respectively, and said internal cooling circuit is a serpentine cooling circuit.

30. An airfoil as claimed in claim 26 wherein said first and second impingement cooling apertures are located along interior corners of said first and second sidewall film cooling chambers.