Non-contacting seals for geared gas turbine engine bearing compartments
A rotating element is associated with at least one bearing compartment that includes a bearing to support the rotating element. A seal resists leakage of lubricant outwardly of the bearing compartment and allows air to flow from a chamber across the seal and into the bearing compartment. The seal has a seal face facing a rotating face rotating with the rotating element. The seal is a non-contact seal. A gas turbine engine is also disclosed.
1. A section for a gas turbine engine comprising:
a rotating element and at least one bearing compartment including a bearing for supporting said rotating element, a seal for resisting leakage of lubricant outwardly of said bearing compartment and for allowing air to flow from a chamber across the seal and into the bearing compartment;
said seal having a seal face facing a rotating face rotating with said rotating element, and said seal being a non-contact seal;
said rotating element is a shaft rotating with a rotor having an axial face facing said seal face;
a grooved area is formed in one of said faces, with said grooved area having a plurality of circumferentially spaced grooves for generating hydrodynamic lift-off forces and allowing leakage of pressurized air across said seal face and into the bearing compartment to resist leakage of lubricant from the bearing compartment; and
said grooved area is formed in said rotor.
2. A section for a gas turbine engine comprising:
a rotating element and at least one bearing compartment including a bearing for supporting said rotating element, a seal for resisting leakage of lubricant outwardly of said bearing compartment and for allowing air to flow from a chamber across the seal and into the bearing compartment;
said seal having a seal face facing a rotating face rotating with said rotating element, and said seal being a non-contact seal; and
said bearing compartment has a seal associated with each of two opposed axial ends, on either axial side of said bearing.
3. The section as set forth in claim 2 , wherein said rotating element is a shaft rotating with a rotor having an axial face facing said seal face.
4. The section as set forth in claim 3 , wherein a grooved area is formed in one of said faces, with said grooved area having a plurality of circumferentially spaced grooves for generating hydrodynamic lift-off forces and allowing leakage of pressurized air across said seal face and into the bearing compartment to resist leakage of lubricant from the bearing compartment.
5. The section as set forth in claim 4 , wherein said grooved area is formed in said rotor.
6. The section as set forth in claim 4 , wherein said seal being formed with a plurality of passages to allow tapping of additional pressurized air to be delivered to the faces at a location in the proximity of the grooved area for generating hydrostatic lift-off forces.
7. A section for a gas turbine engine comprising:
a rotating element and at least one bearing compartment including a bearing for supporting said rotating element, a seal for resisting leakage of lubricant outwardly of said bearing compartment and for allowing air to flow from a chamber across the seal and into the bearing compartment;
said seal having a seal face facing a rotating face rotating with said rotating element, and said seal being a non-contact seal; and
said seal face faces radially inwardly.
8. The section as set forth in claim 7 , wherein said seal is a circumferentially segmented carbon seal.
9. The section as set forth in claim 8 , wherein said rotating element is a shaft rotating with a rotor having a circumferential face facing said seal face.
10. The section as set forth in claim 9 , wherein a grooved area is formed in one of said faces, with said grooved area having a plurality of circumferentially spaced grooves for generating hydrodynamic lift-off forces and allowing leakage of pressurized air across said seal face and into the bearing compartment to resist leakage of lubricant from the bearing compartment.
11. The section as set forth in claim 7 , wherein said seal is a controlled gap carbon seal having a full hoop seal and a metal band shrunk fit onto the seal, and positioned in a seal carrier.
12. The section as set forth in claim 1 , wherein the rotating element is driven by a fan drive turbine.
13. The section as set forth in claim 1 , wherein said seal is a carbon seal.
14. A gas turbine engine comprising:
a fan, a compressor section, a combustor, and a turbine section with a fan drive turbine driving said fan through a gear reduction;
a rotating element and at least one bearing compartment including a bearing for supporting said rotating element, a seal for resisting leakage of lubricant outwardly of said bearing compartment and for allowing pressurized air to flow from a chamber across said seal into the bearing compartment;
said seal having a seal face facing a rotating face rotating with said rotating element, and said seal being a non-contact seal;
said rotating element is a shaft rotating with a rotor having an axial face facing said seal face;
a grooved area is formed in one of said faces, with said grooved area having a plurality of circumferentially spaced grooves for generating hydrodynamic lift-off forces and allowing leakage of pressurized air across said faces and into the bearing compartment to resist leakage of lubricant from the bearing compartment; and
said grooved area is formed in said rotor.
15. A gas turbine engine comprising:
a fan, a compressor section, a combustor, and a turbine section with a fan drive turbine driving said fan through a gear reduction;
a rotating element and at least one bearing compartment including a bearing for supporting said rotating element, a seal for resisting leakage of lubricant outwardly of said bearing compartment and for allowing pressurized air to flow from a chamber across said seal into the bearing compartment;
said seal having a seal face facing a rotating face rotating with said rotating element, and said seal being a non-contact seal; and
said bearing compartment has a seal associated with each of two opposed axial ends, on either axial side of said bearing.
16. The gas turbine engine as set forth in claim 15 , wherein said rotating element is a shaft rotating with a rotor having an axial face facing said seal face.
17. The gas turbine engine as set forth in claim 16 , wherein a grooved area is formed in one of said faces, with said grooved area having a plurality of circumferentially spaced grooves for generating hydrodynamic lift-off forces and allowing leakage of pressurized air across said faces and into the bearing compartment to resist leakage of lubricant from the bearing compartment.
18. The gas turbine engine as set forth in claim 17 , wherein said grooved area is formed in said rotor.
19. The gas turbine engine as set forth in claim 17 , wherein said seal being formed with a plurality of passages to allow tapping of additional pressurized air to be delivered to the faces at a location in the proximity of the grooved area for generating hydrostatic lift-off forces.
20. A gas turbine engine comprising:
a fan, a compressor section, a combustor and a turbine section with a fan drive turbine driving said fan through a gear reduction;
a rotating element and at least one bearing compartment including a bearing for supporting said rotating element, a seal for resisting leakage of lubricant outwardly of said bearing compartment and for allowing pressurized air to flow from a chamber across said seal into the bearing compartment;
said seal having a seal face facing a rotating face rotating with said rotating element, and said seal being a non-contact seal; and
said seal face faces radially inwardly.
21. The gas turbine engine as set forth in claim 20 , wherein said seal is a circumferentially segmented carbon seal.
22. The gas turbine engine as set forth in claim 21 , wherein said rotating element is a shaft rotating with a rotor having a circumferential face facing said seal face.
23. The gas turbine engine as set forth in claim 22 , wherein a grooved area is formed in one of said faces, with said grooved area having a plurality of circumferentially spaced grooves for generating hydrodynamic lift-off forces and allowing leakage of pressurized air across said seal face and into the bearing compartment to resist leakage of lubricant from the bearing compartment.
24. The gas turbine engine as set forth in claim 20 , wherein said seal is a controlled gap carbon seal having a full hoop seal and a metal band shrunk fit onto the seal, and positioned in a seal carrier.
25. The gas turbine engine as set forth in claim 14 , wherein the rotating element is driven by the fan drive turbine.
26. The gas turbine engine as set forth in claim 14 , wherein said seal is a carbon seal.