Axial retention of a platform seal

• US 8,573,942 B2
• Filed: 11/25/2008
• Issued: 11/05/2013
• Est. Priority Date: 11/25/2008
• Status: Active Grant

• Current Assignee: H2 IP UK Limited
• Original Assignee: Alstom Technology Ltd. (Alstom SA)
• Inventors: Strohl, James Page, Rawlings, RuthAnn
• Primary Examiner(s): Parekh, Nitin
• Application Number:
  US12/277,471
• Publication Number:
  US 20100129226A1
• Time in Patent Office: 1,806 Days
• Field of Search: 416/219.R, 416/221, 416/220.R, 277/641, 277/312
• US Class Current: 416/219.R
• CPC Class Codes: F01D 11/006 Sealing the gap between rotor blades or blades and rotor
• CPC Class Codes: F01D 5/22 Blade-to-blade connections, e.g. for damping vibrations
• CPC Class Codes: F01D 5/3007 of axial insertion type
• CPC Class Codes: F05D 2240/80 Platforms for stationary or moving blades
• CPC Class Codes: F16J 15/061 with positioning means F16J15/0831 takes precedence
• CPC Class Codes: F16J 15/0887 the sealing effect being obtained by elastic deformation of the packing

Abstract

A gas turbine engine component having an axial pin stop assembly that reduces stress around a seal pin damper slot between a platform and a buttress is disclosed. The seal pin damper slot is extended to the leading edge of the buttress and an axial pin stop seal extends into the pin damper slot to limit movement of the seal pin damper while relieving stress concentration at the interface between the buttress and platform.

Claims

1. An axial pin seal assembly, comprising:

a substantially axially extending seal pin damper slot extending to a forward face of a buttress;

a substantially radially extending pin stop slot in the buttress and intersecting the seal pin damper slot;

a substantially cylindrical seal pin placed within the seal pin damper slot; and

,

an axial stop pin secured within the pin stop slot;

wherein the axial stop pin limits axial movement of the seal pin.

2. The axial pin seal assembly of claim 1, wherein the pin stop slot and axial stop pin includes a radial retention component.

3. The axial pin seal assembly of claim 2, wherein the axial stop pin is brazed into the pin stop slot.

4. The axial pin seal assembly of claim 1, wherein the axial pin stop partially blocks the seal pin damper slot.

5. The axial pin seal assembly of claim 1, wherein the axial pin stop completely intersects with the seal pin damper slot.

6. The axial pin seal assembly of claim 5, wherein the pin stop slot extends into the platform.

7. The axial seal pin assembly of claim 1, wherein the axial stop pin reduces leakage of a cooling flow passing through the seal pin damper slot.

8. A gas turbine blade assembly comprising:

an attachment;

a neck extending radially outward from the attachment and having one or more buttresses;

a platform extending radially outward from the neck;

a seal pin damper slot extending along a sideface of the platform to a leading edge of the buttress;

a generally radially extending pin stop slot in the buttress and intersecting the seal pin damper slot;

a generally cylindrical seal pin located within the seal pin damper slot; and

,

an axial stop pin fixed within the pin stop slot.

9. The gas turbine blade assembly of claim 8, wherein the seal pin generally blocks air from entering the damper slot.

10. The gas turbine blade assembly of claim 8, wherein the damper slot extends along a majority of an axial length of the platform.

11. The gas turbine blade assembly of claim 8, wherein the damper slot and the pin stop slot are generally perpendicular.

12. The axial pin seal assembly of claim 8, wherein the pin stop slot and axial stop pin include a radial retention component.

13. The axial pin seal assembly of claim 12, wherein the axial stop pin is brazed into the pin stop slot.

14. The axial pin seal assembly of claim 13, wherein the axial stop pin is retained by an adjacent blade.

15. The gas turbine assembly of claim 13, wherein the seal pin can move axially between an end of the seal pin damper slot and the axial stop pin.

16. A method of sealing gaps between adjacent turbine blades in a gas turbine engine, comprising:

undercutting a portion of a buttress proximate its leading edge;

placing a substantially axially extending seal pin damper slot in a buttress and platform region of the turbine blade, wherein the slot extends to a forward face of the turbine blade;

placing a substantially radially extending pin stop slot in the buttress such that the pin stop slot intersects with a seal pin damper slot;

securing an axial stop pin within the pin stop slot; and

,

placing a substantially cylindrical seal pin within the seal pin damper slot.

17. The method of claim 16, wherein the seal pin damper slot and pin stop slot are machined into a cast turbine blade.

18. The method of claim 16, further comprising undercutting a portion of a buttress proximate a pressure side.

19. The method of claim 16, wherein the pin stop slot includes a radial retention feature.

20. The method of claim 16, wherein the seal pin can move axially within the seal pin damper slot.