Locking spacer assembly

Patent metadata

Field	Value
Publication number	US-9341071-B2
Application number	US-201314055124-A
Country	US
Kind code	B2
Filing date	Oct 16, 2013
Priority date	Oct 16, 2013
Publication date	May 17, 2016
Grant date	May 17, 2016

Abstract

Locking spacer assemblies and turbomachines are provided. In one embodiment, a locking spacer assembly includes a spacer, the spacer including a platform and a plurality of legs extending generally radially inward from the platform. The locking spacer assembly further includes a clamp configured to contact and cause elastic deformation of each of the plurality of legs in a generally axial direction towards each other. The locking spacer assembly further includes a locking lug configured to contact and impart a force against each of the plurality of legs in an opposite generally axial direction.

First claim

What is claimed is:

1. A locking spacer assembly for insertion into a circumferential attachment slot between platforms of adjacent rotor blades, comprising:
a spacer, the spacer comprising a platform and a plurality of legs extending generally radially inward from the platform;
a clamp configured to contact and cause elastic deformation of each of the plurality of legs in a generally axial direction towards each other; and
a locking lug configured to contact and impart a force against each of the plurality of legs in an opposite generally axial direction.

2. The locking spacer assembly of claim 1 , wherein each of the plurality of legs comprises a wedge surface and the locking lug comprises wedge having a plurality of mating wedge surfaces, and wherein contact between the wedge surfaces and mating wedge surfaces causes elastic deformation of each of the plurality of legs in the opposite generally axial direction.

3. The locking spacer assembly of claim 2 , wherein the mating wedge surfaces taper in a generally radially outward direction.

4. The locking spacer assembly of claim 1 , wherein the locking lug comprises a rod.

5. The locking spacer assembly of claim 4 , wherein the rod is extendable through a bore hole defined in the platform.

6. The locking spacer assembly of claim 4 , further comprising a fastener connectable to the rod.

7. The locking spacer assembly of claim 1 , wherein each of the plurality of legs comprises a contact surface configured to contact a recessed wall portion of the slot.

8. The locking spacer assembly of claim 1 , wherein the clamp is removable from the plurality of legs.

9. A locking spacer assembly for insertion into a circumferential attachment slot between platforms of adjacent rotor blades, comprising:
a spacer, the spacer comprising a platform and a plurality of legs extending generally radially inward from the platform;
means for elastically deforming each of the plurality of legs in a generally axial direction towards each other; and
a locking lug configured to contact and impart a force against each of the plurality of legs in an opposite generally axial direction.

10. The locking spacer assembly of claim 9 , wherein each of the plurality of legs comprises a wedge surface and the locking lug comprises wedge having a plurality of mating wedge surfaces, and wherein contact between the wedge surfaces and mating wedge surfaces causes elastic deformation of each of the plurality of legs in the opposite generally axial direction.

11. The locking spacer assembly of claim 10 , wherein the mating wedge surfaces taper in a generally radially outward direction.

12. The locking spacer assembly of claim 9 , wherein the locking lug comprises a rod.

13. The locking spacer assembly of claim 12 , wherein the rod is extendable through a bore hole defined in the platform.

14. The locking spacer assembly of claim 12 , further comprising a fastener connectable to the rod.

15. The locking spacer assembly of claim 9 , wherein each of the plurality of legs comprises a contact surface configured to contact a recessed wall portion of the slot.

16. A turbomachine, comprising:
a compressor section;
a turbine section; and
a combustor section between the compressor section and the turbine section,
wherein one of the compressor section or the turbine section comprises:
a rotor disc comprising forward and aft posts defining a continuous circumferentially extending attachment slot;
a plurality of rotor blades, each of the plurality of rotor blades extending from one of a plurality of platforms, wherein each of the plurality of platforms is secured to the attachment slot by an inwardly extending root; and
a locking spacer assembly disposed in a space between at least two of the plurality of platforms, the locking spacer assembly comprising:
a spacer, the spacer comprising a platform and a plurality of legs extending generally radially inward from the platform;
a clamp configured to contact and cause elastic deformation of each of the plurality of legs in a generally axial direction towards each other; and
a locking lug configured to contact and impart a force against each of the plurality of legs in an opposite generally axial direction.

17. The turbomachine of claim 16 , wherein each of the plurality of legs comprises a wedge surface and the locking lug comprises wedge having a plurality of mating wedge surfaces, and wherein contact between the wedge surfaces and mating wedge surfaces causes elastic deformation of each of the plurality of legs in the opposite generally axial direction.

18. The turbomachine of claim 17 , wherein the mating wedge surfaces taper in a generally radially outward direction.

19. The turbomachine of claim 16 , wherein the locking lug comprises a rod.

20. The turbomachine of claim 16 , wherein the clamp is removable from the plurality of legs.

Assignees

• Gen Electric

Inventors

• Healy Michael James
• Potter Brian Denver

Classifications

• F01D5/303 Primary

  in a circumferential slot · CPC title

• F01D5/32 Primary

  Locking, e.g. by final locking blades or keys · CPC title

• F01D5/3038

  the slot having inwardly directed abutment faces on both sides · CPC title