Turbine seals

Patent metadata

Field	Value
Publication number	US-9945484-B2
Application number	US-201113276481-A
Country	US
Kind code	B2
Filing date	Oct 19, 2011
Priority date	May 20, 2011
Publication date	Apr 17, 2018
Grant date	Apr 17, 2018

Abstract

A seal strip ( 60 A, 60 B, 60 C, 60 F, 60 G, 60 H, 60 J) with an imperforate width-spanning portion ( 64 ) first and second rounded edges ( 65, 66 ) and one or more strip-thickening elements ( 67, 68, 74, 76, 82, 84, 90, 91 ) between the rounded edges. The strip-thickening elements may have transverse slots ( 80, 86, 88, 93 L, 93 R, 72, 78 ) for increased flexibility of the strip. The strip-thickening elements may also have perforations ( 92 ) or gaps ( 69 ) to admit coolant and/or to reduce weight. Folded embodiments ( 60 A, 60 B) may have dimples ( 70 ) on the width-spanning portion ( 64 ) to limit bending of the folded portions ( 67, 68, 74, 76 ). The seal may be slidably mounted in opposed slots ( 58 A, 58 B) in respective adjacent turbine components ( 54 A, 54 B), filling a width (W) of the slots, and a side of the seal may be cooled by compressed air ( 48 ).

First claim

The invention claimed is:

1. A seal apparatus comprising:
a strip comprising an imperforate width-spanning portion, first and second rounded edges, and at least one non-woven strip-thickening portion between the rounded edges;
wherein said at least one strip-thickening portion comprises first and second folded portions that are folded inwardly toward each other from the first and second rounded edges respectively over the imperforate width-spanning portion, forming a central gap between proximal edges of the folded portions;
wherein each of said folded portions comprises a series of transverse slots;
wherein the strip is slidably mounted into two opposed slots in two respective adjacent components of a gas turbine, wherein the strip fills a width of the opposed slots, and the central gap is in fluid communication with a cooled area of the gas turbine; and
wherein the imperforate width-spanning portion comprises a plurality of dimples extending toward the folded portions, wherein the dimples limit bending of the folded portions toward the imperforate width-spanning portion.

2. In a gas turbine comprising two adjacent components, and a coolant flow area on one side of the two adjacent components, and a seal apparatus mounted across two respective opposed slots in the two adjacent components, the seal apparatus characterized by:
a strip comprising an imperforate width-spanning portion, first and second rounded edges, and at least one non-woven strip-thickening portion between the rounded edges;
wherein said at least one strip-thickening portion comprises first and second strip-thickening portions extending inward from the respective rounded edges, and further comprising:
a central gap between the first and second strip-thickening portions; and
a series of transverse slots on each of the strip thickening portions, wherein each slot is open to the central gap;
wherein the central gap is in fluid communication with the coolant flow area.

3. The seal apparatus of claim 2 , wherein the first and second rounded edges are hook-shaped in a transverse sectional view of the seal apparatus.

4. In a gas turbine comprising two adjacent components and a coolant flow area, a seal apparatus, comprising:
a strip of material with an imperforate width-spanning portion and a first non-woven strip-thickening portion associated with the width-spanning portion;
the strip comprising first and second opposed rounded edges; and
a perforation, slot or gap formed in the first strip-thickening portion that does not pass through the imperforate width-spanning portion; and
a second non-woven strip-thickening portion associated with the width-spanning portion and comprising a further perforation or slot that does not pass through the imperforate width-spanning portion;
wherein the strip is slidably mounted into two respective opposed slots in the two adjacent turbine components, wherein the first and second strip-thickening portions face the coolant flow area of the gas turbine.

5. The seal of claim 4 wherein the first and second opposed rounded edges and said first and second strip-thickening portions are integrally formed with the width-spanning portion.

6. The seal apparatus of claim 4 , further comprising a sacrificial wear layer disposed on an external surface of the seal apparatus.

Assignees

• Moehrle Frank
• Narcus Andrew R
• Carella John
• Sainte Claire Jean Max Millon
• Siemens Energy Inc

Inventors

• Moehrle Frank
• Narcus Andrew R
• Carella John
• Sainte-Claire Jean-Max Millon

Classifications

• F01D11/005

  Sealing means between non relatively rotating elements · CPC title

• F01D11/003

  by packing rings; Mechanical seals · CPC title

• F16J15/0887 Primary

  the sealing effect being obtained by elastic deformation of the packing · CPC title

• F02C7/28 Primary

  Arrangement of seals · CPC title

• F01D11/00

  Preventing or minimising internal leakage of working-fluid, e.g. between stages (sealings in general F16J {; sealing arrangements for transition ducts of combustor cans F01D9/023}) · CPC title