Curvic seal for use in a gas turbine engine and method of assembling a gas turbine engine

Patent metadata

Field	Value
Publication number	US-9909437-B2
Application number	US-201514959104-A
Country	US
Kind code	B2
Filing date	Dec 4, 2015
Priority date	Dec 4, 2015
Publication date	Mar 6, 2018
Grant date	Mar 6, 2018

Abstract

A curvic seal for use in a gas turbine engine is provided. The curvic seal includes a split ring including a first slit extending therethrough, and a biasing ring coupled to the split ring and extending along a radially inner side thereof. The biasing ring is configured to bias against the split ring and restrict airflow through the first slit.

First claim

What is claimed is:

1. A curvic seal for use in a gas turbine engine, said curvic seal comprising:
a split ring comprising a first slit extending therethrough; and
a biasing ring coupled to said split ring and extending along a radially inner side thereof, said biasing ring configured to bias against said split ring and restrict airflow through said first slit; wherein said split ring comprises:
a pair of side walls extending circumferentially on the radially inner side of said split ring; and
a receiving channel extending between said pair of side walls, wherein said biasing ring extends circumferentially within said receiving channel.

2. The curvic seal in accordance with claim 1 , wherein said biasing ring comprises:
a first portion extending circumferentially within said receiving channel; and
a second portion extending across said first slit and restricting airflow through said first slit.

3. The curvic seal in accordance with claim 2 , wherein said second portion has a width such that side edges of said second portion substantially align with side edges of said split ring.

4. The curvic seal in accordance with claim 2 , wherein said pair of side walls comprise opposing ends separated from each other such that an axial slot is defined therebetween, said opposing ends of said pair of side walls positioned on opposing sides of said first slit.

5. The curvic seal in accordance with claim 4 , wherein said axial slot is sized to receive said second portion therein, said second portion undersized relative to said axial slot in a circumferential direction.

6. A curvic seal for use in a gas turbine engine, said curvic seal comprising:
a split ring comprising a first slit extending therethrough; and
a biasing ring coupled to said split ring and extending along a radially inner side thereof, said biasing ring configured to bias against said split ring and restrict airflow through said first slit; wherein said biasing ring comprises a second slit extending therethrough, said second slit offset from said first slit when said biasing ring is coupled to said split ring.

7. A gas turbine engine comprising:
a curvic coupling positioned between a first rotating component and a second rotating component of the gas turbine engine; and
a curvic seal positioned radially inward from said curvic coupling, said curvic seal comprising:
a split ring comprising a first slit extending therethrough; and

a biasing ring coupled to said split ring and extending along a radially inner side thereof, said biasing ring configured to bias against said split ring and restrict airflow through said first slit; wherein said split ring comprises:
a pair of side walls extending circumferentially on the radially inner side of said split ring; and
a receiving channel extending between said pair of side walls, wherein said biasing ring extends circumferentially within said receiving channel.

8. The gas turbine engine in accordance with claim 7 , wherein said biasing ring comprises:
a first portion extending circumferentially within said receiving channel; and
a second portion extending across said first slit and restricting airflow through said first slit.

9. The gas turbine engine in accordance with claim 8 , wherein said second portion has a width such that side edges of said second portion substantially align with side edges of said split ring.

10. The gas turbine engine in accordance with claim 9 , wherein said pair of side walls comprise opposing ends separated from each other such that an axial slot is defined therebetween, said opposing ends of said pair of side walls positioned on opposing sides of said first slit.

11. The gas turbine engine in accordance with claim 10 , wherein said axial slot is sized to receive said second portion therein, said second portion undersized relative to said axial slot in a circumferential direction.

12. The gas turbine engine in accordance with claim 11 , wherein said biasing ring comprises a second slit extending therethrough, said second slit offset from said first slit when said biasing ring is coupled to said split ring.

13. A method of assembling a curvic seal for use in a gas turbine engine, said method comprising:
defining a radially inner side of a split ring having a first slit extending therethrough; and
coupling a biasing ring to the split ring such that the biasing ring extends along the radially inner side of the split ring, the biasing ring configured to bias against the split ring and restrict airflow through the first slit; wherein coupling a biasing ring comprises extending the biasing ring circumferentially within a receiving channel defined between a pair of side walls that extend circumferentially on the radially inner side of the split ring.

14. The method in accordance with claim 13 , wherein coupling a biasing ring comprises:
extending a first portion of the biasing ring circumferentially within the receiving channel; and
configuring a second portion of the biasing ring to extend across the first slit and restrict airflow therethrough.

15. The method in accordance with claim 14 , wherein coupling a biasing ring comprises substantially aligning side edges of the second portion with side edges of the split ring.

16. The method in accordance with claim 14 further comprising defining an axial slot between opposing ends of the pair of side walls, the axial slot sized to receive the second portion of the biasing ring therein.

17. The method in accordance with claim 16 further comprising sizing the second portion such that the second portion is undersized relative to the axial slot in a circumferential direction.

Assignees

• Gen Electric

Inventors

• Hubley Christopher Karl
• Qader Khalil
• Park Sang Yeng

Classifications

• F05D2220/30

  in turbines · CPC title

• F05D2240/55

  Seals · CPC title

• F16J15/0887

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

• F01D11/005

  Sealing means between non relatively rotating elements · CPC title

• F16J15/067 Primary

  Split packings · CPC title