Gas turbine engine vane and method of manufacture

• US 5,797,725 A
• Filed: 05/23/1997
• Issued: 08/25/1998
• Est. Priority Date: 05/23/1997
• Status: Expired due to Term

• Current Assignee: Rolls-Royce North American Technologies Incorporated
• Original Assignee: Rolls-Royce North American Technologies Incorporated
• Inventors: Rhodes, Jeffrey F.
• Primary Examiner(s): KWON, JOHN
• Application Number:
  US08/862,837
• Time in Patent Office: 459 Days
• Field of Search: 415/209.1, 415/209.2, 415/209.3, 415/209.4
• US Class Current: 415/209.2
• CPC Class Codes: B23P 6/005 using only replacement pieces of a particular form
• CPC Class Codes: F01D 9/042 fixing blades to stators fixing stator-rings in the casing or to each other F01D25/246
• CPC Class Codes: F05D 2230/60 Assembly methods

Abstract

A gas turbine engine vane and method of manufacture. In one form of the present invention a vane is non destructively removeable from a vane segment to allow individual components to be replaced. The vane and endwalls are coupled together by a retainer that is formed in place between the vane and the endwall and that can be removed by conventional techniques. In one form the retainer fills a pair of corresponding grooves in the vane and endwall member so as to mechanically couple the components together and minimize fluid leakage therebetween. The retainer being nonmetallurgically coupled to the vane and endwall member. A portion of the vane being allowed to move relative to the endwall in response to thermal conditions.

Claims

1. A gas turbine engine vane, comprising:

an airfoil having an outer surface extending between a leading edge and a trailing edge and between a first end and an opposite other second end;

an endwall positioned proximate one of said ends; and

a retainer formed insitu and extending between said airfoil and said endwall for coupling said airfoil with said endwall, said retainer abutting but not bonded to said endwall and said airfoil.

2. The vane of claim 1, wherein said retainer is cast.

3. The vane of claim 1, wherein said retainer is forged.

4. The vane of claim 1, wherein said endwall has an aperture therein for receiving said one of said ends therein, and wherein said retainer positioned so as to abut the portion of said airfoil extending into said aperture.

5. The vane of claim 4, wherein said endwall has reinforcing ribs proximate said aperture.

6. The vane of claim 1, wherein said airfoil is a cast structure.

7. The vane of claim 6, wherein said endwall is a cast structure, and wherein said airfoil is substantially hollow.

8. The vane of claim 1, wherein:

said endwall is a cast structure formed of a superalloy having an aperture formed therein;

said airfoil is hollow cast structure formed of a superalloy; and

said retainer abutting a portion of said airfoil that is positioned within said aperture, and said retainer is of a metal material.

9. The vane of claim 8, wherein said airfoil and endwall are of a single crystal alloy structure.

10. The vane of claim 9, wherein said retainer is cast.

11. The vane of claim 9, wherein said retainer is forged.

12. The vane of claim 8, wherein said airfoil and said endwall are of a directionally solidified alloy structure.

13. The vane of claim 12, wherein said retainer is cast.

14. The vane of claim 12, wherein said retainer is forged.

15. The vane of claim 8, comprising another endwall positioned proximate the other of said ends, and further including retainer formed insitu and extending between said airfoil and said another endwall, said retainer abutting but not bonded to said another endwall and said airfoil, and wherein said endwalls and said airfoil have been preoxidized.

16. The vane of claim 15, wherein said another endwall has an aperture formed therein for receiving the other of said ends therein, said retainer positioned so as to abut a portion of said airfoil extending into said aperture in said another endwall.

17. The vane of claim 16, wherein said airfoil is a hollow casting formed of a superalloy, and wherein said another endwall is formed of a superalloy.

18. The vane of claim 17, wherein said retainers are forged, and wherein said endwalls and said airfoil are of a single crystal alloy structure.

19. The vane of claim 17, wherein said retainers are forged, and wherein said endwalls and said airfoil are of a single crystal alloy structure.

20. The vane of claim 17, which further includes a plurality of airfoils coupled to said endwalls by a plurality of retainers.

21. A gas turbine engine vane, comprising:

a wall member; and

an airfoil having an outer surface extending between a leading edge and a trailing edge and between a first end and an opposite other second end, said airfoil having a first portion and a second portion along one of said ends, said first portion fixedly coupled by a retainer to said wall member and said second portion being moveable relative to said wall member.

22. The vane of claim 21, wherein said retainer is formed insitu.

23. The vane of claim 22, wherein said retainer is cast.

24. The vane of claim 23, wherein said retainer is forged.

25. The vane of claim 22, wherein said retainer has a retaining portion and a sealing portion, said retaining portion couples said airfoil first portion to said wall member, and said sealing portion defining a mechanical seal for abutting said airfoil second portion and said wall member to provide a mechanical seal.

26. The vane of claim 22, wherein said retainer retaining portion extending from said leading edge around said airfoil to a position spaced from said trailing edge.

27. The vane of claim 26, wherein said airfoil has a length, and wherein said retaining portion is spaced from said trailing edge a distance in the range of about 20% to about 40% of said length.

28. The vane of claim 26, wherein said airfoil has a length, and wherein said retaining portion is spaced from said trailing edge a distance of about one third of the length of said airfoil.

29. The vane of claim 21, wherein said second portion is moveable relative to the wall member in response to thermal conditions.

30. The vane of claim 21:

wherein said retainer is formed insitu;

wherein said retainer has a retaining portion for coupling said first portion to said wall member and a sealing portion defining a mechanical seal for abutting said second portion and said wall member to normally provide a mechanical seal, said retaining portion extending from said leading edge around said airfoil to a location spaced from said trailing edge, said location is within a range of about 20% to 40% of the length said airfoil.

31. The vane of claim 21:

which further includes another wall member;

said first end and second end of the airfoil being substantially identical;

which further includes another retainer for fixedly coupling a first portion of said other end of said airfoil to said another wall member and said second portion of said other end being moveable relative to said another wall member; and

wherein said wall members defining an endwall.

32. The vane of claim 31, which further includes a plurality of airfoils, each of said plurality of airfoils being coupled at a first endwall member at a first portion by said retainer and said second portion being moveable relative to said member, and each of said plurality of airfoils being coupled at a second end to said another wall member at a first portion by a retainer and said second portion being moveable relative to said another wall member.

33. A gas turbine engine vane, comprising:

an airfoil having an outer surface extending between a leading edge and a trailing edge and between a first end and an opposite other second end, said airfoil having a first groove therein at one of said ends extending along at least a portion of said outer surface between said leading edge and said trailing edge;

an endwall having a second groove therein, said endwall positioned proximate said airfoil so that said first and second grooves are substantially in registry; and

a retainer filling said grooves and extending between said airfoil and said endwall for coupling but not bonding said airfoil with said endwall.

34. The vane of claim 33, wherein said retainer fills substantially one hundred percent of said grooves.

35. The vane of claim 33, wherein said first and second grooves are rectangular.

36. The vane of claim 35, wherein a width of each said first and second grooves range from about 0.05 inches to about 0.100 inches.

37. The vane of claim 36, wherein the width of said first and second grooves is not equal.

38. The vane of claim 33, wherein said first and second grooves are semi-circular.

39. The vane of claim 38, wherein a diameter of each of said first and second grooves ranges from about 0.05 inches to 0.10 inches.

40. The vane of claim 39, wherein the diameter of one of said grooves is greater than the diameter of the other of said grooves.

41. The vane of claim 33, wherein said endwall has an aperture for receiving one end of said airfoil therein, and wherein said groove formed on a wall member defining said aperture.

42. The vane of claim 41, wherein said second groove extends completely along the wall member defining said aperture.

43. The vane of claim 42, wherein said first groove extends from said leading edge to a position spaced from said trailing edge.

44. The vane of claim 41:

further including a second endwall having an aperture for receiving the other end of said airfoil therein, and wherein a third groove is formed on a wall member defining the aperture of said second airfoil;

said other end of said airfoil having a fourth groove therein that extends along at least a portion of said outer surface between said leading edge and said trailing edge;

said second endwall positioned proximate said other end of said airfoil so that said third and fourth grooves are substantially in registry for receiving a second retainer to fill said third and fourth grooves for coupling but not bonding said airfoil with said second endwall.

45. The vane of claim 44, which further includes a plurality of airfoils coupled but not bonded to said endwalls.

46. A method for assembling a vane segment, comprising:

providing an airfoil having an outer surface extending between a first end and an opposite other second end and having a first groove therein at one of said ends, further providing a wall member having a second groove therein;

positioning the wall member and one of the ends of the airfoil so that the first and second grooves are substantially in registry; and

placing a retainer adaptable to the shape of the grooves within the grooves for coupling but not bonding the airfoil to the endwall.

47. The method of claim 46, wherein said providing includes a second wall member having a groove therein, and which further includes peroxiding the airfoil and the wall member.

48. The method of claim 46, wherein said placing includes casting the retainer insitu.

49. The method of claim 46, wherein said placing includes forging the retainer insitu.

50. The method of claim 46, wherein said placing includes filling the grooves to about one hundred percent with the retainer.

51. The method of claim 46, which further includes obtaining a vane segment that has been run prior to said providing, which further includes separating the airfoil and endwall that are coupled but not bonded prior to said providing, and which further includes selecting the resuseable component prior to said providing.

52. The method of claim 51, wherein said separating includes chemical removal of the retainer from the grooves.

53. The method of claim 51, wherein said separating includes electro-discharge machining of the retainer so as to substantially remove the retainer from the grooves.