Turbine split ring retention and anti-rotation method

Patent metadata

Field	Value
Publication number	US-9567857-B2
Application number	US-201314035617-A
Country	US
Kind code	B2
Filing date	Sep 24, 2013
Priority date	Mar 8, 2013
Publication date	Feb 14, 2017
Grant date	Feb 14, 2017

Abstract

A gas turbine engine disk split retainer ring system is provided and includes an apparatus and method for retaining a split ring in relation to a turbine cover plate or disk. Pegs are used to capture and retain a split retainer ring of the gas turbine rotor in relation to the cover plate. An anti-rotation peg has a radially oriented tab for engaging the split ring so as to control the rotation of the ring. The system may be used to balance the operating condition of a turbo machine.

First claim

What is claimed is:

1. A disk arrangement for a gas turbine engine comprising:
a disk with a bayonet feature;
a cover plate with a bayonet feature;
a split retainer ring;
an anti-rotation peg having a first surface for engaging the split retainer ring,
a second surface for engaging the cover plate, and a third surface for engaging the disk; and
a radial retention peg,
wherein the anti-rotation peg includes at least one of:
a radially-oriented tab that projects from a surface and engages an opening in the retainer ring; or
a stop that engages the retainer ring and prevents the retainer ring from rotating relative to the disk and the cover plate.

2. The disk arrangement for a gas turbine engine as claimed in claim 1 , wherein the disk includes an arcuate shaped opening, and the cover plate includes an arcuate shaped opening, the openings may be aligned to receive a peg.

3. The disk arrangement for a gas turbine engine as claimed in claim 1 , wherein the split retainer ring is substantially L-shaped from a side sectional view perspective, and is substantially C-shaped from a front view perspective.

4. The disk arrangement for a gas turbine engine as claimed in claim 1 , wherein the split retainer ring has a first surface for engaging the cover plate, and a second surface for engaging the radial retention peg, the split retainer ring radially retains the pegs in the opening between the bayonet features of the disk and cover plate.

5. The disk arrangement for a gas turbine engine as claimed in claim 1 , wherein the split retainer ring retains the pegs in a slot that is created by the bayonet feature of at least one of the disk and cover plate.

6. The disk arrangement for a gas turbine engine as claimed in claim 1 , wherein the anti-rotation peg includes a radial outer surface for engaging a radial inner surface of the cover plate.

7. The disk arrangement for a gas turbine engine as claimed in claim 1 , wherein the radial retention peg includes an L-shaped surface that mates with a corresponding L-shaped surface of the split retainer ring.

8. The disk arrangement for a gas turbine engine as claimed in claim 1 , further comprising a plurality of radial retention pegs, each said peg being inserted into an aperture that is created by the bayonet features of the disk and cover plate.

9. A system for a gas turbine engine comprising:
an annular shaped disk having a plurality of openings;
a cover plate having a member that extends within an opening in the disk;
an anti-rotation peg having a surface that engages the cover plate;
at least one radial retention peg having a surface that engages the cover plate; and
a retainer member sandwiched between the cover plate and the radial retention peg,
wherein the anti-rotation peg includes at least one of:
a radially-oriented tab that projects from a surface and engages an opening in a retainer ring; or
a stop that engages the retainer ring and prevents the retainer ring from rotating relative to the disk and the cover plate.

10. The system as claimed in claim 9 , wherein the anti-rotation peg has the radially-oriented tab that projects from the surface, wherein the tab engages the opening in the retainer ring.

11. The system as claimed in claim 9 , wherein the anti-rotation peg has the stop that engages the retainer ring and prevents the retainer ring from rotating relative to the disk and the cover plate.

12. The system as claimed in claim 9 , wherein the anti-rotation peg can be removed from the system, which allows the retainer ring to be rotated to a new position, and the anti-rotation peg can then be inserted into another opening in the disk to position the retainer ring into place.

13. The system as claimed in claim 9 , wherein the cover plate has a cavity with an L-shaped wall that substantially mates with a corresponding L-shaped wall of the retainer member.

14. The system as claimed in claim 9 , wherein the retainer ring is split.

15. The system as claimed in claim 9 , wherein the retainer ring has a first surface for axially engaging the cover plate, the retainer ring has a second surface for radially engaging the cover plate.

16. The system as claimed in claim 9 , further comprising a plurality of radial retention pegs, each such peg positioned in an opening in the disk.

17. The system as claimed in claim 9 , wherein the system is a high or low pressure turbine.

18. A method of a gas turbine machine comprising steps of:
providing a disk, a cover plate, an anti-rotation peg, at least one radial retention peg, and a retainer ring;
positioning a portion of the cover plate into a cavity of the disk;
inserting the radial retention peg into a cavity of the disk;
inserting the anti-rotation peg into the cavity of the disk; and
inserting the retainer ring,
whereby the anti-rotation peg prevents the retainer ring from rotating
wherein the anti-rotation peg includes at least one of:
a radially-oriented tab that projects from a surface and engages an opening in the retainer ring; or
a stop that engages the retainer ring and prevents the retainer ring from rotating relative to the disk and the cover plate.

19. The method as claimed in claimed 18 , wherein the retainer ring includes a split ring, and further comprising the step of correcting imbalance of the gas turbine machine, the correcting imbalance step includes removing the anti-rotation peg, advancing the split ring in a clockwise or counter-clockwise direction, and then reinserting the anti-rotation peg into an aperture.

20. The method as claimed in claimed 18 , further comprising the step of determining a turbo machine unbalanced condition, and then adjusting the positioning of one or more radial retention pegs relative to the disk so as to create a balanced-like condition of the turbo machine.

Assignees

• Rolls Royce Nam Tech Inc

Inventors

• Snyder Brandon R

Classifications

• F01D11/001

  for sealing space between stator blade and rotor · CPC title

• F05D2260/36

  by a form fit connection, e.g. by interlocking · CPC title

• F01D5/3015

  with side plates · CPC title

• F05D2240/24

  for turbines · CPC title

• F05D2250/182

  crenellated, notched · CPC title