Systems and methods for improving start up wear performance of carbon seals

Patent metadata

Field	Value
Publication number	US-11255205-B2
Application number	US-201916293383-A
Country	US
Kind code	B2
Filing date	Mar 5, 2019
Priority date	Mar 5, 2019
Publication date	Feb 22, 2022
Grant date	Feb 22, 2022

Abstract

An improved face seal may comprise a seal housing having an annular extrusion, and a primary seal coupled to the seal housing. The primary seal comprises a sealing face and a base opposite the sealing face, wherein the primary seal has an annular structure coaxial with the annular extrusion with the base proximate a first end of the seal housing. The sealing face comprises a disrupted surface.

First claim

What is claimed is:

1. An improved face seal, comprising:
a seal housing comprising an annular extrusion; and
a primary seal coupled to the seal housing,
wherein the primary seal comprises a sealing face and a base opposite the sealing face,
wherein the primary seal has an annular structure coaxial with the annular extrusion with the base proximate a first end of the seal housing,
wherein the sealing face comprises a disrupted surface extending over the sealing face,
wherein the disrupted surface comprises a patterned portion,
wherein the patterned portion comprises a plurality of ablated portions having a depth below the sealing face between 0.381 μm to 12.7 μm,
wherein the patterned portion includes the plurality of ablated portions having a spacing between each of a relatively adjacent ablated portion of the plurality of ablated portions between 0.08 mm and 0.25 mm, and
wherein the disrupted surface is configured to promote the transfer of a seal material from the sealing face to a seating face in response to rotation of the seating face against the sealing face.

2. The improved face seal of claim 1 , further comprising a seal support, wherein the annular extrusion is disposed within the seal support, wherein the annular extrusion comprises a secondary seal at a distal end of the annular extrusion opposite the primary seal.

3. The improved face seal of claim 1 , wherein the patterned portion comprises the plurality of ablated portions having an Ra between 0.381 μm to 2.667 μm.

4. The improved face seal of claim 1 , wherein the patterned portion comprises the plurality of ablated portions having an Rz between 2.413 μm to 11.43 μm.

5. A gas turbine engine comprising:
a compressor section configured to compress a gas;
a combustor section aft of the compressor section configured to combust the gas;
a turbine section aft of the combustor section configured to extract work from the gas; and
an improved face seal, comprising:
a seal housing comprising an annular extrusion; and
a primary seal coupled to the seal housing,
wherein the primary seal comprises a sealing face and a base opposite the sealing face,
wherein the primary seal has an annular structure coaxial with the annular extrusion having the base proximate a first end of the seal housing,
wherein the sealing face comprises a disrupted surface extending over the sealing face,
wherein the disrupted surface comprises a patterned portion,
wherein the patterned portion comprises a plurality of ablated portions having a depth below the sealing face between 0.381 μm to 12.7 μm,
wherein the patterned portion includes the plurality of ablated portions having a spacing between each of a relatively adjacent ablated portion of the plurality of ablated portions between 0.08 mm and 0.25 mm, and
wherein the disrupted surface is configured to promote the transfer of a seal material from the sealing face to a seating face in response to rotation of the seating face against the sealing face.

6. The gas turbine engine of claim 5 , further comprising a seal support, wherein the annular extrusion is disposed within the seal support, wherein the annular extrusion comprises a secondary seal at a distal end of the annular extrusion opposite the primary seal.

7. The gas turbine engine of claim 5 , wherein the patterned portion comprises the plurality of ablated portions having an Ra between 0.381 μm to 2.667 μm.

8. The gas turbine engine of claim 5 , wherein the patterned portion comprises the plurality of ablated portions having an Rz between 2.413 μm to 11.43 μm.

9. An article of manufacture including a carbon face seal having a disrupted surface thereon, the disrupted surface comprising:
a patterned portion defined by a plurality of ablated portions on a sealing face of the carbon face seal,
wherein the plurality of ablated portions have a depth below the sealing face between 0.381 μm to 12.7 μm,
wherein the plurality of ablated portions have a spacing between each of a relatively adjacent ablated portion of the plurality of ablated portions between 0.08 mm and 0.25 mm,
wherein the plurality of ablated portions have an Ra between 0.381 μm to 2.667 μm,
wherein the disrupted surface extends over the sealing face of the carbon face seal, and
wherein the disrupted surface is configured to promote the transfer of a seal material from the sealing face to a seating face in response to rotation of the seating face against the sealing face.

10. The article of manufacture of claim 9 , wherein the plurality of ablated portions have an Rz between 2.413 μm to 11.43 μm.

Assignees

• United Technologies Corp
• Raytheon Tech Corp

Inventors

• Ranganath Santosh
• Kilguss Andrew C
• Ogden William P
• Hammond James P

Classifications

• F01D11/005

  Sealing means between non relatively rotating elements · CPC title

• F01D11/003 Primary

  by packing rings; Mechanical seals · CPC title

• F16J15/3424

  with microcavities · CPC title

• F01D25/183

  Sealing means · CPC title

• F05D2240/55

  Seals · CPC title