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US 11,035,253 B2Granted
Face seal with damper
AssigneeRaytheon Technologies Corporation
InventorBrady Walker
Life of this patent
Estimating the term…
Abstract
A gas turbine engine component includes a static component, a seal body associated with the static component, the seal body having an end surface configured to face a rotating seal seat, and a damper positioned radially outward of the seal body. The damper includes a contact that engages the seal body to dampen radial movement of the seal body while accommodating axial movement of the seal body.
Claims20
A gas turbine engine component comprising:
- a static component that comprises a seal housing fixed to a non-rotating engine structure;
- a seal body associated with the static component, the seal body having an end surface configured to face a rotating seal seat that rotates about an engine center axis;
- a seal carrier fixed to the seal body;
- at least one spring acting between the seal housing and the seal body to accommodate axial movement of the seal body relative to the rotating seal seat;
- and
- a damper positioned radially outward of the seal body, wherein the damper includes a contact that engages the seal body to dampen radial movement of the seal body while accommodating axial movement of the seal body, and wherein the damper comprises at least one finger extending from the seal housing in an axial direction along the engine center axis to a distal end that extends in a radial inward direction toward the seal carrier.
3 more elements
A gas turbine engine comprising:
- at least one rotor shaft that interconnects a compressor and a turbine for rotation about an engine center axis;
- and
- a carbon face seal assembly including a seal housing fixed to a non-rotating engine structure, a seal seat mounted for rotation with the at least one rotor shaft, a seal body postioned axially between the seal housing and the seal seat, and a damper positioned radially outward of the seal body, wherein the damper includes a contact that engages the seal body to dampen radial movement of the seal body while accommodating axial movement of the seal body, wherein the damper comprises at least one finger extending from the seal housing in an axial direction along the engine center axis to a distal end that extends in a radial inward direction toward the seal body.
A method of operating a gas turbine comprising the steps of:
- driving at least one shaft with a turbine rotor to drive a compressor;
- holding a seal body in a non-rotating relationship relative to a rotating seal seat coupled to the at least one shaft;
- and
- damping radial movement of the seal body with a damper positioned radially outward of the seal body while accommodating axial movement of the seal body relative to the rotating seal seat, wherein the damper includes a contact that engages the seal body to dampen radial movement of the seal body while accommodating axial movement of the seal body, and including rotating the contact within the damper to accommodate the axial movement, and pivoting the damper via a pivoting area to allow the damper to move up and down in a radial direction to accommodate the radial movement.
1 more element
A gas turbine engine component comprising:
- a static component;
- a seal body associated with the static component, the seal body having an end surface configured to face a rotating seal seat;
- and
- a damper positioned radially outward of the seal body, wherein the damper includes a contact that engages the seal body to dampen radial movement of the seal body while accommodating axial movement of the seal body, wherein the contact rotates within the damper to accommodate the axial movement, and wherein the damper includes a pivoting area that allows the damper to move up and down in a radial direction to accommodate the radial movement.
1 more element
Dependencies are inferred from the claim text.