Turbine blade damper and seal

• US 5,827,047 A
• Filed: 06/27/1996
• Issued: 10/27/1998
• Est. Priority Date: 06/27/1996
• Status: Expired due to Term

• Current Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Original Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Kelley, Sanford E. III, Houston, David P., Gonsor, Michael
• Primary Examiner(s): VERDIER, CHRISTOPHER M
• Application Number:
  US08/671,462
• Time in Patent Office: 852 Days
• Field of Search: 416/193 A, 416/190, 416/219 R, 416/220 R, 416/221, 416/248, 416/500
• US Class Current: 416/193.00A
• CPC Class Codes: F01D 11/006 Sealing the gap between rotor blades or blades and rotor
• CPC Class Codes: F01D 11/008 by spacer elements between the blades, e.g. independent interblade platforms
• CPC Class Codes: F01D 5/22 Blade-to-blade connections, e.g. for damping vibrations
• CPC Class Codes: F01D 5/26 Antivibration means not restricted to blade form or construction or to blade-to-blade connections or to the use of particular materials
• CPC Class Codes: Y10S 416/50 Vibration damping features

Abstract

A damper for a turbine blade in a gas turbine engine includes a main body and may include at least one extended end which is adapted to clear radially inner surfaces of two adjacent blade platforms, to enhance the damping profile of the damper and radial support for a seal. An associated seal for the turbine blade includes supported and sealing portions and may further include a locator that interfaces with a catch structure on the blade to maintain the seal in the proper axial position with respect to the radially inner surfaces of the adjacent platforms. The seal may further include a projection adapted to provide interference with the blade in the event that the damper and seal are installed improperly with respect to each other to prevent such improper assembly.

Claims

1. A rigid vibration damper for use with two adjacent turbine rotor blades in a gas turbine engine, each turbine rotor blade having an airfoil portion, a platform, a neck, and a root, the blade platforms each having a radially outer surface, and a radially inner surface connected by the blade neck to the blade root, the radially inner surface having a damping portion a sealing portion radially inward of the damping portion, and a transition portion disposed between the damping and the sealing portions, the rigid damper comprising:

a main body having a damping surface adapted to contact the damping portion of the radially inner surface of each blade platform and to provide a friction force on the damping portions; and

at least one end axially extended from said main body, and adapted to clear the transition and the sealing portions of the radially inner surfaces of each blade platform.

2. The damper of claim 1 wherein said at least one end is free.

3. The damper of claim 1 wherein said damping surface of said main body is substantially planar.

4. The damper of claim 1 wherein each of said at least one end has an axial length that is less than or equal to about one half that of the main body.

5. The damper of claim 1 wherein the sealing portion comprises a radially inward skirt.

6. The damper of claim 1 wherein the transition portion of the radially inner surfaces has an arcuate contour and each of said at least one extended end is tapered, gradually reducing in thickness.

7. The damper of claim 6 wherein the transition portion of the radially inner surfaces provides a roughly ninety degree bend.

8. The damper of claim 1 wherein said damping surface of said main body is substantially planar and each of said at least one end is free is tapered and gradually reducing in thickness, and has axial length that is about one half that of the main body, and wherein the sealing portion of the radially inner surfaces comprises a radially inward skirt and the transition portion of the radially inner surfaces has an arcuate contour.

9. The damper of claim 8 wherein the transition portion of the radially inner surfaces provides a roughly ninety degree bend.

20. The apparatus of claim 8 wherein said at least one extended end extends said damper in an axial direction.

21. The apparatus of claim 20 wherein said at least one end is free.

22. The apparatus of claim 20 wherein said damping surface of said main body is substantially planar.

23. The apparatus of claim 20 wherein each of said at least one end has an axial length that is about one half that of the main body.

24. The apparatus of claim 20 wherein the transition portion of the radially inner surfaces has an arcuate contour and each of said at least one end is tapered, gradually reducing in thickness.

25. The apparatus of claim 24 wherein the transition-portion of the radially inner surfaces provides a roughly ninety degree bend.

10. A damping and sealing apparatus for use with two adjacent turbine blades, each blade having an airfoil, a platform a neck, and a root, the blade platforms each having a radially outer surface supporting the airfoil, and a radially inner surface connected by the blade neck to the blade root, the radially inner surface having a damping portion, a sealing portion, and a transition portion located between the damping and the sealing portions, the apparatus comprising:

a flexible seal, having at least one sealing portion extending from a supported portion, said at least one sealing portion adapted to provide sealing in combination with the sealing portion of the adjacent blade platform radially inner surfaces; and

a rigid damper, having at least one end extending from a main body, said at least one extended end and said main body disposed between the adjacent blade platform radially inner surfaces and said supported portion of said seal, said main body having a damping surface in contact with the damping portion of the radially inner surfaces and adapted to provide a friction force on the damping portions, said at least one extended end being of a length sufficient to clear the adjacent platform radially inner surfaces, and said main body and said at least one extended end each having a support surface in contact with said supported portion of said seal and adapted to provide support therefor.

11. The apparatus of claim 10 wherein said at least one extended end extends said damper in an axial direction.

12. The apparatus of claim 11 wherein said damping surface of said main body is substantially planar and each of said at least one end is free is tapered and gradually reducing in thickness, and has an axial length that is about one half that of the main body, and wherein the sealing portion of the radially inner surfaces comprises a radially inward skirt and the transition portion of the radially inner surfaces has an arcuate contour.

13. The apparatus of claim 12 wherein the transition portion of the radially inner surfaces provides a roughly ninety degree bend.

14. The apparatus of claim 10 wherein said at least one extended end is tapered.

15. The apparatus of claim 10 wherein the transition portion includes upstream and downstream fillet runouts and said at least one extended end comprises a pair of tapered ends which extends said damper in an axial direction from the upstream fillet runout to the downstream fillet runout.

16. The apparatus of claim 10 wherein said support surface of said damper has a substantially planar surface.

17. The apparatus of claim 10 wherein said damping and said support surfaces of said damper have substantially planar surfaces, and said support surface is generally opposed to said damping surface.

18. The apparatus of claim 10 wherein said supported portion of said flexible seal further comprises a locator which interfaces with one of the blades when the flexible seal is installed, to positively position and maintain the flexible seal axially relative to the blade.

19. The apparatus of claim 18 wherein said flexible seal further comprises a projection extending from said supported portion which provides an interference when the flexible seal and the damper are installed in improper relation to each other.

26. The apparatus of claim 18 wherein the transition portion includes forward and rear fillet runouts and said at least one extended end comprises a pair of extended ends which extends said damper in an axial direction from the forward fillet runout to the rear fillet runout.

27. The apparatus of claim 16 wherein said support surface of said damper has a substantially planar surface opposed said damping surface of said damper.

28. The apparatus of claim 27 wherein said at least one sealing portion of said flexible seal comprises a pair of sealing portions and said supported portion of said flexible seal is substantially planar, said seal having an arcuate bend disposed between said supported portion and each of said sealing portions.

29. The apparatus of claim 18 wherein one of the blades has a catch on its neck for said interface between said locator and the blade.

30. The apparatus of claim 29 wherein the catch comprises a pair of standoffs and the locator comprises a notch.

31. The apparatus of claim 30 wherein said flexible seal further comprises a tab projecting from said supported portion which provides an interference with one of the blades when the flexible seal and the damper are installed in improper relation to each other.

32. The apparatus of claim 31 wherein said damping surface of said main body is substantially planar and each of said at least one end is free, extends said damper in an axial direction, is tapered and gradually reducing in thickness, and has an axial length that is about one half that of the main body, and wherein the sealing portion of the radially inner surfaces comprises a radially inward skirt and the transition portion of the radially inner surfaces has an arcuate contour.

33. The apparatus of claim 32 wherein the transition portion of the radially inner surfaces provides a roughly ninety degree bend.

34. The apparatus of claim 10 wherein said supported portion of said flexible seal further comprises a notch which interfaces with one of the blades when the flexible seal is installed, to positively position and maintain the flexible seal axially relative to the blade.

35. The apparatus of claim 34 wherein said flexible seal further comprises a tab projecting from said supported portion which provides an interference with one of the blades when the flexible seal and the damper are installed in improper relation to each other.

36. The apparatus of claim 10 wherein said flexible seal further comprises a projection extending from said supported portion which provides an interference when the flexible seal and the damper are installed in improper relation to each other.

37. The apparatus of claim 10 wherein said flexible seal further comprises a tab projecting from said supported portion which provides an interference with one of the blades when the flexible seal and the damper are installed in improper relation to each other.

38. The apparatus of claim 10 wherein said at least one sealing portion of said flexible seal comprises a pair of sealing portions and said supported portion of said flexible seal is substantially planar, said seal having an arcuate bend disposed between said supported portion and each of said sealing portions.

39. The apparatus of claim 10 wherein said at least one end is free.

40. The apparatus of claim 10 wherein said damping surface of said main body is substantially planar.

41. The apparatus of claim 10 wherein each of said at least one extended end has an axial length that is about one half that of the main body.

42. The apparatus of claim 10 wherein the transition portion of the radially inner surfaces has an arcuate contour and each of said at least one end is tapered and gradually reducing in thickness.

43. The apparatus of claim 42 wherein the transition portion of the radially inner surfaces provides a roughly ninety degree bend.

44. An apparatus for two adjacent turbine blades in a gas turbine engine, each blade having an airfoil, a platform, a neck, and a root, the blade platforms each having a radially outer surface supporting the airfoil, and a radially inner surface connected by the blade neck to the blade root, the radially inner surface itself having a damping portion, a sealing portion, and a transition portion located between the damping and sealing portions, the damping portion generally facing the disk, the apparatus comprising:

a flexible seal, having at least one sealing portion joined to a supported portion, said at least one sealing portion adapted to provide sealing in combination with the sealing portion of the adjacent blade platform radially inner surfaces, said seal further having a projection joined to said supported portion;

a rigid damper, disposed between the adjacent blade platform radially inner surfaces and said supported portion of said seal, said damper having a damping surface in contact with the damping portion of the radially inner surfaces and adapted to provide a friction force on the damping portions, said damper having a support surface in contact with said supported portion of said seal and adapted to provide support for the seal, and said projection of said seal providing an interference with one of the blades when said damper and said seal are installed in improper relation to each other.

45. A flexible seal for use with two adjacent turbine rotor blades in a gas turbine engine, each blade having an airfoil, a platform a neck, and a root the blade platforms each hawk a radially outer surface supporting the airfoil and a radially inner surface connected by the blade neck to the blade root, the radially inner surface itself having a sealing portion one of the blades having a catch on its neck, the flexible seal comprising:

a supported portion adapted to receive radial support for the seal, said supported portion having a locator which interfaces with the catch when the flexible seal is installed in the adjacent blades to positively position and maintain the flexible seal in an axial position with respect to the radially inner surfaces of the blade platforms; and

at least one sealing portion joined to said, supported portion and adapted to provide sealing in combination with the sealing portion of the adjacent blade platform radially inner surfaces;

wherein the catch includes a standoff.

46. The flexible seal of claim 45 wherein said locator comprises a notched edge.

47. The flexible seal of claim 45 wherein said locator comprises a notch and the catch includes a pair of standoffs adapted to position the seal in a circumferential direction relative to the neck.

48. The flexible seal of claim 47 wherein the neck has a concave surface on which said standoffs are located and said notch has a generally curving rectangular-like shape.

49. A flexible seal for use with two adjacent turbine rotor blades and a rigid damper in a gas turbine engine each blade having an airfoil, a platform, a neck, and a root the blade platforms each having a radially outer surface supporting the airfoil, and a radially inner surface connected by the blade neck to the blade root the radially inner surface itself having a damping portion and a sealing portion, the damper having a damping surface and a support surface, the damping surface being adapted to contact with and provide a friction force on the damping portion of the radially inner surface of each blade platform, one of the blades having a catch on its neck the flexible seal comprising:

a supported portion adapted to receive radial support from the support surface of the damper, said supported portion having a locator which interfaces with the catch when the flexible seal is installed in the adjacent blades, to positively position and maintain the flexible seal in an axial position with respect to the radially inner surfaces of the blade platforms, and

at least one sealing portion joined to said supported portion and adapted to provide sealing in combination with the sealing portion of the adjacent blade platform radially inner surfaces.

50. The flexible seal of claim 49 wherein said locator comprises a notch.

51. The flexible seal of claim 49 wherein the catch includes a standoff.

52. The flexible seal of claim 49 wherein said locator comprises a notch and the catch includes a pair of standoffs adapted to position the seal in a circumferential direction relative to the neck.

53. The flexible seal of claim 52 wherein the neck has a concave surface on which the standoffs are located and said notch has a generally curving rectangular-like shape.