Turbine disk attachment system

• US 5,288,210 A
• Filed: 01/21/1993
• Issued: 02/22/1994
• Est. Priority Date: 10/30/1991
• Status: Expired due to Term

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Albrecht, Richard W., Weisgerber, Robert H., Kutney, John T. Jr.
• Primary Examiner(s): KWON, JOHN
• Application Number:
  US08/008,243
• Time in Patent Office: 397 Days
• Field of Search: 416/198 R, 416/198 A, 416/204 R, 416/204 A
• US Class Current: 416/198.00A
• CPC Class Codes: F01D 5/066 Connecting means for joining rotor-discs or rotor-elements together, e.g. by a central bolt, by clamps

Abstract

A disk attachment system for a high pressure turbine section of a gas turbine engine, the high pressure turbine section including a first stage disk and a second stage disk. The first stage disk includes a first conical aft shaft extending rearwardly from a bore of the first state disk and the second stage disk has a second conical aft shaft extending rearwardly from a bore of the second stage disk, and the second aft shaft is attached to the first aft shaft at a splined connection. The second aft shaft includes an arm having a mate face and pilot for centering the second stage disk relative to the first stage disk. Rotational energy from the second stage disk is transmitted through the first aft shaft to the first stage disk.

Claims

1. In a gas turbine engine of a type having a high pressure turbine section including a first stage disk and a second stage disk, adjacent to said first stage disk, a disk attachment system comprising:

said first stage disk including a rearwardly-extending first aft shaft which supports said second stage disk; and

said second stage disk having means for mounting said second stage disk on said first aft shaft, whereby rotational energy from said second stage disk is transmitted through said first aft shaft to said first stage disk and said second stage disk is removable from said gas turbine engine independently of said first stage disk.

2. The system of claim 1 wherein said first aft shaft extends rearwardly from a bore of said first stage disk.

3. The system of claim 2 wherein said mounting means includes a second rearwardly-extending portion non-rotatably attached to said first aft shaft.

4. The system of claim 3 wherein said second rearwardly-extending portion includes a second conical aft shaft, extending rearwardly from a bore of said second stage disk and being concentric with said first aft shaft.

5. The system of claim 4 wherein said second aft shaft is attached to said first aft shaft at a splined connection.

6. The system of claim 1 wherein said first conical aft shaft extends rearwardly from a bore of said first stage disk.

7. The system of claim 6 wherein said second stage disk mounting means includes a second rearwardly-extending portion non-rotatably attached to said first aft shaft.

8. The system of claim 7 wherein said second rearwardly-extending portion includes a second conical aft shaft, extending rearwardly from a bore of said second stage disk and being concentric with said first aft shaft.

9. The system of claim 8 wherein said second aft shaft is attached to said first aft shaft at a splined connection.

10. In a gas turbine engine of a type having a high pressure turbine section including a first stage disk and a second stage disk, adjacent to said first stage disk a disk attachment system comprising:

said first stage disk including a first conical aft shaft extending rearwardly from a bore of said first stage disk;

said second stage disk having a second conical aft shaft, extending rearwardly from a bore of said second stage disk and being concentric with said first aft shaft;

said second aft shaft is attached to said first aft shaft at a splined connection;

said second aft shaft includes an arm terminating in means for centering said second stage disk relative to said first stage disk, whereby rotational energy from said second stage disk is transmitted through said first aft shaft to said first stage disk.

11. The system of claim 10 wherein said centering means includes a mate face and pilot;

and said first aft shaft includes location means for receiving said mate face and pilot.

12. The system of claim 11 wherein said arm extends toward said first aft shaft such that said centering means is positioned intermediate said second stage disk and said splined connection.

13. The system of claim 12 wherein said centering means is positioned beyond an attenuation point of said second aft shaft.

14. The system of claim 13 wherein said splined connection is shaped to provide longitudinal cooling air passages.

15. The system of claim 14 further comprising means for securing said second stage disk against axial movement relative to said first stage disk.

16. The system of claim 15 wherein said securing means includes a locking nut threaded on said first aft shaft and abutting an aft end of said second aft shaft.

17. The system of claim 16 further comprising an aft seal having a web engaging a web of said second stage disk;

and a bore engaging said second aft shaft.

18. The system of claim 17 further comprising a sump seal engaging said aft seal bore and said locking nut.

19. The system of claim 18 wherein said sump seal includes means engaging said locking nut for preventing rotation of said locking nut.

20. The system of claim 19 wherein said sump seal includes a rear wall having forwardly projecting, radially-extending teeth;

and said locking nut includes radially-extending grooves receiving said teeth.

21. The system of claim 20 wherein said sump seal engages said second aft shaft in a bayonet connection.

22. In a gas turbine engine of a type having a high pressure turbine section including a first stage disk and a second stage disk, adjacent to said first stage disk, a disk attachment system comprising:

said first stage disk including a first aft shaft extending rearwardly from a bore of said first stage disk;

said second stage disk having a second conical aft shaft, extending rearwardly from a bore of said second stage disk and being concentric with said first aft shaft;

said second aft shaft is attached to said first aft shaft at a splined connection whereby rotational energy from said second stage disk is transmitted through said first aft shaft to said first stage disk; and

said second aft shaft includes an arm terminating in means for centering said second stage disk relative to said first stage disk.

23. The system of claim 22 wherein said centering means includes a mate face and pilot;

and said first aft shaft includes location means for receiving said mate face and pilot.

24. The system of claim 23 wherein said arm extends toward said first aft shaft such that said centering means is positioned intermediate said second stage disk and said splined connection.

25. The system of claim 24 wherein said centering means is positioned beyond an attenuation point of said second aft shaft.

26. The system of claim 25 wherein said splined connection is shaped to provide cooling air passages.

27. The system of claim 26 further comprising means for securing said second stage disk against axial movement relative to said first stage disk.

28. The system of claim 27 wherein said securing means includes a locking nut threaded on said first aft shaft and abutting an aft end of said second aft shaft.

29. The system of claim 28 further comprising an aft seal having a forward shaft engaging a web of said second stage disk;

and a bore engaging said second aft shaft.

30. The system of claim 29 further comprising a sump seal engaging said aft seal bore and said locking nut.

31. The system of claim 30 wherein said sump seal includes means engaging said locking nut for preventing rotation of said locking nut.

32. The system of claim 31 wherein said sump seal includes a rear wall having forwardly projecting, radially-extending teeth;

and said locking nut includes radially-extending grooves receiving said teeth.

33. The system of claim 32 wherein said sump seal engages said second aft shaft in a bayonet connection.

34. The system of claim 33 wherein said sump seal and said aft seal each include tabs along a contiguous border therebetween, said tabs being in meshing relation;

and said second aft shaft includes tabs aligned with said aft seal tabs and meshing with said sump seal tabs to prevent relative rotation between said aft seal, said sump seal and said second aft shaft.