Cooled turbine rim seal

• US 8,382,432 B2
• Filed: 03/08/2010
• Issued: 02/26/2013
• Est. Priority Date: 03/08/2010
• Status: Active Grant

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Grissino, Alan Scott, Wigon, Jeremy Stephen, Busso, Gianni Emanuolo
• Primary Examiner(s): Kershteyn, Igor
• Application Number:
  US12/719,222
• Publication Number:
  US 20110217158A1
• Time in Patent Office: 1,086 Days
• Field of Search: 415/115, 415/175, 415/178, 415/199.5, 416/95, 416/96.R, 416/198.A
• US Class Current: 416/95
• CPC Class Codes: F01D 11/001 for sealing space between stator blade and rotor
• CPC Class Codes: F16J 15/44 Free-space packings

Abstract

A rim seal assembly includes an annular seal element circumscribing an engine centerline or axis and mounted on an annular platform including a radially inwardly extending annular platform flange disposed between and connected to forward and aft flanges at distal ends of forward and aft annular elements respectively. Annular forward and aft outer rim cavities radially disposed between the forward and aft annular elements and the platform are axially separated by the platform flange. Cooling slots extend radially across axially facing forward and aft surfaces of the forward and aft flanges. The platform flange and the forward and aft flanges are bolted together. The annular seal element may include seal teeth in sealing relationship with an annular seal land such as in a labyrinth seal. The rim seal assembly may be incorporated in a low pressure turbine use a compressor as a source of cooling air.

Claims

1. A rim seal assembly comprising:

an annular seal element circumscribing an engine centerline or axis and mounted on an annular platform,

an annular platform flange extending radially inwardly from the platform,

the platform flange disposed between and connected to forward and aft flanges at distal ends of forward and aft annular elements respectively,

annular forward and aft outer rim cavities radially disposed between the forward and aft annular elements and the platform are axially separated by the platform flange, and

cooling slots extending radially across axially facing forward and aft surfaces of the forward and aft flanges.

2. A rim seal assembly as claimed in claim 1, further comprising the platform flange and the forward and aft flanges being bolted together.

3. A rim seal assembly as claimed in claim 2, further comprising the annular seal element being seal teeth.

4. A rim seal assembly as claimed in claim 3, further comprising the seal teeth in sealing relationship with an annular seal land.

5. A rim seal assembly comprising:

an annular seal element circumscribing an engine centerline or axis and mounted on an annular platform,

an annular platform flange extending radially inwardly from the platform,

the platform flange disposed between and connected to forward and aft flanges at distal ends of forward and aft annular elements respectively of a high pressure rotor or a low pressure rotor,

annular forward and aft outer rim cavities radially disposed between the forward and aft annular elements and the platform are axially separated by the platform flange, and

cooling slots extending radially across axially facing forward and aft surfaces of the forward and aft flanges.

6. A rim seal assembly as claimed in claim 5, further comprising the platform flange and the forward and aft flanges being bolted together.

7. A rim seal assembly as claimed in claim 6, further comprising the annular seal element being seal teeth.

8. A rim seal assembly as claimed in claim 7, further comprising the seal teeth in sealing relationship with an annular seal land.

9. A gas turbine engine turbine disk assembly comprising:

at least one pair of adjacent first and second rotor disks connected by disk forward and aft spacer arms attached to the adjacent first and second rotor disks respectively,

at least one rim seal assembly including an annular seal element circumscribing an engine centerline or axis and mounted on an annular platform,

an annular platform flange extending radially inwardly from the platform,

the platform flange disposed between and connected to forward and aft flanges at distal ends of the forward and aft spacer arms respectively,

annular forward and aft outer rim cavities radially disposed between the forward and aft spacer arms and the platform are axially separated by the platform flange, and

cooling slots extending radially across axially facing forward and aft surfaces of the forward and aft flanges.

10. A gas turbine engine turbine disk assembly as claimed in claim 9, further comprising the platform flange and the forward and aft flanges being bolted together.

11. A gas turbine engine turbine disk assembly as claimed in claim 10, further comprising the annular seal element being seal teeth.

12. A gas turbine engine turbine disk assembly as claimed in claim 11, further comprising the seal teeth in sealing relationship with an annular seal land.

13. A gas turbine engine turbine disk assembly comprising:

a plurality of rotor disks,

each of the rotor disks including a web extending radially outwardly from a hub to a disk rim,

the plurality of rotor disks including at least one pair of adjacent first and second rotor disks connected by disk forward and aft spacer arms attached to the adjacent first and second rotor disks respectively,

turbine blades extending radially outwardly from the disk rim of the adjacent first and second rotor disks,

a row of vanes extending radially inwardly from a case and disposed axially between the turbine blades of the adjacent first and second rotor disks,

an annular seal land mounted to a radially inner end of the row of vanes,

at least one rim seal assembly including an annular seal element circumscribing an engine centerline or axis and mounted on an annular platform,

the annular seal element in sealing relationship with the annular seal land,

an annular platform flange extending radially inwardly from the platform,

the platform flange disposed between and connected to forward and aft flanges at distal ends of the forward and aft spacer arms respectively,

annular forward and aft outer rim cavities radially disposed between the forward and aft spacer arms and the platform are axially separated by the platform flange, and

cooling slots extending radially across axially facing forward and aft surfaces of the forward and aft flanges.

14. A gas turbine engine turbine disk assembly as claimed in claim 13, further comprising a bore disposed radially inwardly of the hub and the forward and aft spacer arms and in flow communication with a source of cooling air.

15. A gas turbine engine turbine disk assembly as claimed in claim 14, further comprising the turbine blades and the row of vanes extending radially across a low pressure turbine primary flowpath.

16. A gas turbine engine turbine disk assembly as claimed in claim 15, further comprising the source of cooling air being a compressor.

17. A gas turbine engine comprising:

in downstream serial flow relationship, a fan, a compressor, a combustor, a high pressure turbine, and a low pressure turbine,

a plurality of rotor disks in the low pressure turbine,

each of the rotor disks including a web extending radially outwardly from a hub to a disk rim,

the plurality of rotor disks including at least one pair of adjacent first and second rotor disks connected by disk forward and aft spacer arms attached to the adjacent first and second rotor disks respectively,

turbine blades extending radially outwardly from the disk rim of the adjacent first and second rotor disks,

a row of vanes extending radially inwardly from a case and disposed axially between the turbine blades of the adjacent first and second rotor disks,

an annular seal land mounted to a radially inner end of the row of vanes,

at least one rim seal assembly including an annular seal element circumscribing an engine centerline or axis and mounted on an annular platform,

the annular seal element in sealing relationship with the annular seal land,

an annular platform flange extending radially inwardly from the platform,

the platform flange disposed between and connected to forward and aft flanges at distal ends of the forward and aft spacer arms respectively,

annular forward and aft outer rim cavities radially disposed between the forward and aft spacer arms and the platform are axially separated by the platform flange, and

cooling slots extending radially across axially facing forward and aft surfaces of the forward and aft flanges.

18. A gas turbine engine turbine disk assembly as claimed in claim 17, further comprising a bore disposed radially inwardly of the hub and the forward and aft spacer arms and in flow communication with a source of cooling air.

19. A gas turbine engine turbine disk assembly as claimed in claim 18, further comprising the turbine blades and the row of vanes extending radially across a low pressure turbine primary flowpath.

20. A gas turbine engine turbine disk assembly as claimed in claim 19, further comprising the source of cooling air being a compressor.