Component lock for a gas turbine engine

• US 8,840,375 B2
• Filed: 03/21/2011
• Issued: 09/23/2014
• Est. Priority Date: 03/21/2011
• Status: Active Grant

• Current Assignee: Rtx Corporation
• Original Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Virkler, Scott D.
• Primary Examiner(s): Look, Edward
• Assistant Examiner(s): BROCKMAN, ELDON T
• Application Number:
  US13/053,134
• Publication Number:
  US 20120244004A1
• Time in Patent Office: 1,282 Days
• Field of Search: 416/220.R, 416/221, 416/219.R, 416/204.R, 416/204.A
• US Class Current: 416/221
• CPC Class Codes: F01D 5/066 Connecting means for joining rotor-discs or rotor-elements together, e.g. by a central bolt, by clamps
• CPC Class Codes: F01D 5/08 Heating, heat-insulating or cooling means specially adapted for radial flow machines or engines F01D5/04
• CPC Class Codes: F01D 5/3015 with side plates
• CPC Class Codes: F05D 2250/131 polygonal
• CPC Class Codes: F05D 2250/132 hexagonal
• CPC Class Codes: F05D 2260/36 by a form fit connection, e.g. by interlocking
• CPC Class Codes: Y10T 29/49234 Rotary or radial engine making
• CPC Class Codes: Y10T 70/50 Special application

Abstract

A lock assembly includes a lock body with an undercut slot which receives a retaining wire of a polygon shape.

Claims

1. A rotor disk assembly for a gas turbine engine comprising:

a rotor disk defined about an axis of rotation, said rotor disk having a circumferentially intermittent slot structure that extends radially outward relative to said axis of rotation;

a component defined about said axis of rotation, said component having a multiple of radial tabs which extend radially inward relative to said axis of rotation, said multiple of radial tabs engageable with said circumferentially intermittent slot structure; and

a lock assembly engaged with at least one opening formed by said circumferentially intermittent slot structure to provide an anti-rotation interface for said component, said lock assembly comprising a retaining wire that defines a polygon shape.

2. The rotor disk assembly as recited in claim 1, wherein said component is a heat shield.

3. The rotor disk assembly as recited in claim 2, wherein said heat shield separates a relatively hotter outer diameter cavity from a relatively cooler inner diameter cavity.

4. The rotor disk assembly as recited in claim 3, wherein said heat shield spans an interface.

5. The rotor disk assembly as recited in claim 4, wherein said interface is a splined interface between a high pressure turbine and a high pressure compressor.

6. The rotor disk assembly as recited in claim 1, wherein said circumferentially intermittent slot structure extends radially outward from a cylindrical extension from said rotor disk.

7. The rotor disk assembly as recited in claim 1, wherein the rotor disk is a turbine rotor disk.

8. The rotor disk assembly as recited in claim 1, wherein said polygon shape is a substantially hexagonal shape.

9. The rotor disk assembly as recited in claim 1, wherein said retaining wire includes a plurality of linear segments, one of which includes a gap.

10. The rotor disk assembly as recited in claim 9, wherein said retaining wire includes rounded portions between said linear segments.

11. The rotor disk assembly as recited in claim 10, wherein at least one of said rounded portions is captured between said circumferentially intermittent slot structure.

12. The rotor disk assembly as recited in claim 1, wherein said lock assembly comprises a lock body that has an undercut slot, said retaining wire is received within said undercut slot.

13. The rotor disk assembly as recited in claim 1, wherein said lock assembly includes a lock tab, said lock tab protrudes substantially perpendicularly from a lock body of said lock assembly and abuts at least one of said radial tabs.

14. A method to assemble a rotor disk assembly comprising:

locating a cover plate adjacent to a rotor disk along an axis of rotation;

axially locating a heat shield having a multiple of radial tabs which extend radially inward relative to the axis of rotation, the multiple of radial tabs axially aligned with openings defined by a circumferentially intermittent slot structure on the rotor disk;

rotating the heat shield to radially align the multiple of radial tabs with the circumferentially intermittent slot structure to axially retain the cover plate to the rotor disk; and

engaging a lock assembly that has a retaining wire that defines a polygon shape with the circumferentially intermittent slot structure to provide an anti-rotation interface for the heat shield.

15. A method as recited in claim 14, further comprising:

resiliently compressing the retaining wire of the lock assembly and inserting the compressed retaining wire into the circumferentially intermittent slot structure.

16. A method as recited in claim 14, further comprising:

spanning an interface with the heat shield.

17. A method as recited in claim 14, further comprising:

spanning a splined interface between a high pressure turbine and a high pressure compressor.

18. A rotor disk assembly for a gas turbine engine comprising:

a rotor disk defined about an axis of rotation, said rotor disk having a circumferentially intermittent slot structure that extends radially outward relative to said axis of rotation;

a component defined about said axis of rotation, said component having a multiple of radial tabs which extend radially inward relative to said axis of rotation, said multiple of radial tabs engageable with said circumferentially intermittent slot structure; and

a lock assembly comprising a resilient retaining wire that can be compressed such that said compressed resilient retaining wire can engage with at least one opening formed by said circumferentially intermittent slot structure to provide an anti-rotation interface for said component, said resilient retaining wire defining a polygon shape.