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A seal assembly for a bearing assembly in a gas turbine engine includes a first annular runner disposed around a shaft rotatable about an axis defining an axial direction. The first annular runner is rotatable with the shaft about the axis. A seal element is spaced apart from the first annular runne

A seal assembly for a bearing assembly in a gas turbine engine includes a first annular runner disposed around a shaft rotatable about an axis defining an axial direction. The first annular runner is rotatable with the shaft about the axis. A seal element is spaced apart from the first annular runner and cooperating therewith to provide a gap seal. An annular lip axially extends from the gap seal to an open end. The lip is disposed at least partially around the seal runner. A second annular runner is disposed coaxially with and spaced radially apart from the lip. The second annular runner extends axially opposite to the lip so as to provide a tortuous path leading to the open end of the lip. A restrictor extends between the lip and the second annular runner to impede the passage oil through the tortuous path to the open end of the lip.

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1. A seal assembly for a bearing assembly in a gas turbine engine, the seal assembly comprising: an annular runner including a first annular runner portion and a second annular runner portion, the annular runner disposed around a shaft rotatable about an axis defining an axial direction, the annular

1. A seal assembly for a bearing assembly in a gas turbine engine, the seal assembly comprising: an annular runner including a first annular runner portion and a second annular runner portion, the annular runner disposed around a shaft rotatable about an axis defining an axial direction, the annular runner rotatable with the shaft about the axis;a seal element axially aligned with, radially superposed with and radially spaced apart from the first annular runner portion and cooperating therewith to provide a gap seal axially aligned with the seal element and the first annular runner portion;an annular lip axially extending from the gap seal to an open end, the annular lip disposed at least partially around the annular runner;the second annular runner portion axially extending from the first annular runner portion and disposed coaxially with and spaced radially apart from the annular lip, the second annular runner portion extending axially opposite to the annular lip so as to provide a tortuous path leading to the open end of the annular lip; anda restrictor extending between the annular lip and the second annular runner portion to impede a passage of oil through the tortuous path to the open end of the annular lip. 2. The seal assembly of claim 1, wherein the second annular runner portion is disposed radially outwardly of the annular lip. 3. The seal assembly of claim 1, wherein the annular lip extends generally parallel to the first annular runner portion. 4. The seal assembly of claim 1, wherein the restrictor is a lip portion extending generally radially from the annular lip of the seal assembly toward the second annular runner portion. 5. The seal assembly of claim 1, wherein the restrictor is disposed at the open end of the annular lip of the seal assembly. 6. The seal assembly of claim 1, wherein the second annular runner portion includes an arcuate first portion, and a straight second portion extending from the arcuate first portion. 7. The seal assembly of claim 6, wherein the second portion of the second annular runner portion extends generally parallel to the annular lip. 8. The seal assembly of claim 6, wherein the restrictor is a lip portion extending radially from the annular lip toward the first portion of the second annular runner portion. 9. The seal assembly of claim 1, wherein the gap seal is a dual controlled gap carbon seal directing pressurised air toward a pressurized air chamber, the dual controlled gap carbon seal being connected to an end of the annular lip opposite to the open end. 10. The seal assembly of claim 1, wherein the restrictor and the second annular runner define a pressurized air chamber. 11. A tilt-rotor gas turbine engine comprising the seal assembly of claim 1, the engine rotatable between a horizontal and a vertical position, and wherein the second annular runner portion extends towards a lower end of the gas turbine engine when it is in the vertical position. 12. An aircraft tilt-rotor gas turbine engine assembly moveable between a horizontal operating position where a centerline of the engine is aligned to the body centerline of the aircraft, and a vertical operating position where the centerline of the engine is transverse to a centerline of the body of the aircraft, the gas turbine comprising: a bearing disposed around a rotating shaft, the shaft defining an axial direction;an annular bearing chamber incorporating the bearing, the annular bearing chamber including: an annular bearing cavity being a reservoir; andan annular seal assembly disposed around the shaft, the seal assembly opening into the reservoir of the bearing cavity, the seal assembly sealing an annular space between the reservoir of the annular bearing chamber and the rotating shaft whether the engine is in the vertical position, in the horizontal position, or a position in between. 13. The gas turbine engine of claim 12, wherein the seal assembly includes an annular lip extending from a seal element and spaced apart from an annular runner, an annular arcuate runner disposed around the annular lip, and a restrictor disposed between the annular lip and the annular arcuate runner, the seal element cooperating with the annular runner to provide a gap seal, the annular lip and the annular arcuate runner defining a pressurised air chamber preventing oil to leak from the bearing cavity. 14. The gas turbine engine of claim 13, wherein the gap seal is a dual controlled gap carbon seal directing pressurised air toward the pressurized air chamber, the dual controlled gap carbon seal being connected to an end of the annular lip. 15. The gas turbine engine of claim 14, wherein the dual controlled gap carbon seal includes a first chamber, and the pressurized air chamber is a second chamber. 16. The gas turbine engine of claim 13, wherein the annular lip extends generally parallel to the annular runner. 17. The gas turbine engine of claim 13, wherein the annular lip includes a first portion extending generally axially, and a second portion extending from the first portion and converging axially. 18. The gas turbine engine of claim 13, wherein the restrictor is a lip extending radially from the annular lip toward the annular arcuate runner. 19. The gas turbine engine of claim 13, wherein the restrictor is disposed at an open end of the annular lip.