Radial seal arrangement with axially elongated oil cooled runner
A seal includes a seal runner, at least one seal ring, and a seal housing. The runner extends in an axial direction to a runner end face that faces a bearing. The ring is fixed to a static structure and has an inner surface engaging the seal runner and a first face that faces the bearing. The seal housing is fixed to the static structure and includes a first portion extending in an axial direction from the first face of the seal ring to a housing face that faces the bearing. The first portion has a first length extending from the first face of the seal ring to the housing face. The seal runner has a first runner portion with a second length that extends from the first face of the seal ring to the runner end face. The second length is at least 35% longer than the first length.
1. A gas turbine engine component comprising:
at least one bearing to support a shaft for rotation about an engine axis, wherein the at least one bearing is positioned within a bearing compartment; and
a seal assembly to provide sealing for the bearing compartment, wherein the seal assembly includes
a seal runner that rotates about the engine axis, and wherein the seal runner extends in an axial direction to a runner end face that faces the at least one bearing,
at least one seal ring fixed to an engine static structure and having a radially inner surface engaging the seal runner and a first end face that faces the at least one bearing,
a seal housing fixed to the engine static structure, and wherein the seal housing includes a first housing portion extending in an axial direction from the first end face of the at least one seal ring to a housing end face that faces the at least one bearing,
wherein the first housing portion has a first axial length extending from the first end face of the at least one seal ring to the housing end face, and wherein the seal runner has a first runner portion that has a second axial length that extends from the first end face of the at least one seal ring to the runner end face, and wherein the second axial length is at least 35% longer than the first axial length, and
wherein the first runner portion includes a radially outer surface with a plurality of chopper slots spaced circumferentially apart from each other, and wherein the plurality of chopper slots do not extend through a thickness of the first runner portion.
2. The gas turbine engine component according to claim 1 , wherein the second axial length is at least 50% longer than the first axial length.
3. The gas turbine engine component according to claim 1 , wherein the first housing portion includes a radially inner surface with a plurality of protrusions that face the plurality of chopper slots.
4. The gas turbine engine component according to claim 1 , wherein the first runner portion includes a retention lip that extends in a radially inward direction at the runner end face.
5. The gas turbine engine component according to claim 4 , wherein the first runner portion includes a plurality of exit holes extending through the first runner portion from a radially inner surface to the radially outer surface, and wherein the plurality of exit holes are axially spaced apart from the retention lip.
6. The gas turbine engine component according to claim 5 , wherein the plurality of exit holes comprises a single row of holes that are circumferentially spaced apart from each other about the engine axis.
7. The gas turbine engine component according to claim 4 , wherein the retention lip includes a plurality of scallops formed within a radially inner surface of the first runner portion.
8. The gas turbine engine component according to claim 1 , wherein the at least one bearing includes an inner race fixed for rotation with the shaft and an outer race fixed to the engine static structure, and wherein the runner end face is surrounded by at least one of the inner race and outer race in a radially overlapping relationship.
9. The gas turbine engine component according to claim 1 , wherein the at least one seal ring comprises at least two seal rings with a first seal ring that has the first end face that faces the at least one bearing and that has a second end face that faces a second seal ring, and wherein the seal housing includes a second housing portion that abuts against the second seal ring such that the first and second housing portions cooperate to enclose the first and second seal rings in a cavity formed between the seal housing and the seal runner.
10. The gas turbine engine component according to claim 1 , wherein the plurality of chopper slots are axially spaced from the at least one seal ring in a direction along the engine axis.
11. The gas turbine engine component according to claim 9 , wherein the seal runner includes a second runner portion that extends from the first end face of the first seal ring to a distal end that extends in a radially inward direction toward the shaft, and wherein the first runner portion is radially spaced apart from the shaft and the distal end engages the shaft.
12. A gas turbine engine component comprising:
at least one bearing to support a shaft for rotation about an engine axis, wherein the at least one bearing is positioned within a bearing compartment; and
a seal assembly to provide sealing for the bearing compartment, wherein the seal assembly includes
a seal runner that rotates about the engine axis, and wherein the seal runner extends in an axial direction to a runner end face that faces the at least one bearing,
at least one seal ring fixed to an engine static structure and having a radially inner surface engaging the seal runner and a first end face that faces the at least one bearing,
a seal housing fixed to the engine static structure, and wherein the seal housing includes a first housing portion extending in an axial direction from the first end face of the at least one seal ring to a housing end face that faces the at least one bearing, and wherein the seal housing includes a second housing portion that receives the at least one seal ring,
wherein the first housing portion has a first axial length extending from the first end face of the at least one seal ring to the housing end face, and wherein the seal runner has a first runner portion that has a second axial length that extends from the first end face of the at least one seal ring to the runner end face, and wherein the second axial length is longer than the first axial length,
wherein the first runner portion includes a retention lip that extends in a radially inward direction at the runner end face, and wherein the first runner portion includes a plurality of holes and/or a plurality of scallops, and
wherein the first runner portion includes a radially outer surface with a plurality of chopper slots spaced circumferentially apart from each other, and wherein the plurality of chopper slots do not extend through a thickness of the first runner portion.
13. The gas turbine engine component according to claim 12 , wherein the plurality of holes comprises a plurality of exit holes extending through the first runner portion from a radially inner surface to the radially outer surface, and wherein the plurality of exit holes are axially spaced apart from the retention lip.
14. The gas turbine engine component according to claim 13 , wherein the plurality of exit holes comprises a single row of holes that are circumferentially spaced apart from each other about the engine axis.
15. The gas turbine engine component according to claim 12 , wherein the plurality of scallops formed within a radially inner surface of the first runner portion.
16. The gas turbine engine component according to claim 12 , wherein the second axial length is at least 35% longer than the first axial length.
17. The gas turbine engine component according to claim 12 , wherein the second axial length is at least 50% longer than the first axial length.
18. The gas turbine engine component according to claim 12 , wherein the first housing portion includes a radially inner surface with a plurality of protrusions that face the plurality of chopper slots.
19. The gas turbine engine component according to claim 12 , wherein the at least one seal ring comprises at least two seal rings with a first seal ring that has the first end face that faces the at least one bearing and that has a second end face that faces a second seal ring, and wherein the second housing portion abuts against the second seal ring such that the first and second housing portions cooperate to enclose the first and second seal rings in a cavity formed between the seal housing and the seal runner, and wherein the seal runner includes a second runner portion that extends from the first end face of the first seal ring to a distal end that extends in a radially inward direction toward the shaft, and wherein the first runner portion is radially spaced apart from the shaft and the distal end engages the shaft.
20. The gas turbine engine component according to claim 12 , wherein the plurality of chopper slots are axially spaced from the at least one seal ring in a direction along the engine axis.