Gas turbine engine including seal plate providing increased cooling adjacent contact area
AssigneeUnited Technologies Corporation
InventorMark F. Zelesky
Life of this patent
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Abstract
A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a compressor section, a combustor section, a turbine section, and at least one rotatable shaft. The engine further includes a seal assembly including a seal plate mounted for rotation with the rotatable shaft and a face seal in contact with the seal plate at a contact area. The seal plate includes a cooling passageway having a circumferentially-extending section radially aligned with the contact area.
Claims24
A gas turbine engine, comprising:
- a compressor section, a combustor section, a turbine section, and at least one rotatable shaft;
- and
- a seal assembly including a seal plate mounted for rotation with the rotatable shaft and a face seal in contact with the seal plate at a contact area, the seal plate including a cooling passageway having a circumferentially-extending section radially aligned with the contact area. wherein the cooling passageway includes an inlet section between an inlet and the circumferentially-extending section, wherein the cooling passageway includes an outlet section between the circumferentially-extending section and as a outlet;
- and
- a source of cooling fluid, wherein the seal plate is arranged such that the cooling fluid flows through the cooling passageway from the inlet to the outlet, wherein the cooling passageway is arranged such that the cooling fluid turns substantially ninety degrees as the cooling fluid exits the inlet section and enters the circumferentially-extending section, wherein the cooling passageway is arranged such that the cooling fluid turns substantially ninety degrees as the cooling fluid exits the circumferentially-extending section and enters the outlet section, and wherein the circumferentially-extending section is substantially rectangular in cross-section including a width in an axial direction and a height in a radial direction greater than the width.
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A bearing compartment for a gas turbine engine, comprising:
- a bearing assembly;
- and
- a seal assembly including a seal plate and a face seal in contact with the seal plate at a contact area, the seal plate including a cooling passageway having a circumferentially-extending section radially aligned with the contact area, wherein the cooling passageway includes an inlet section between an inlet and the circumferentially-extending section, wherein the cooling passageway includes an outlet section between the circumferentially-extending section and an outlet;
- and
- a source of cooling fluid, wherein the seal plate is arranged such that the cooling fluid flows through the cooling passageway front the inlet to the outlet, wherein the cooling passageway is arranged such that the cooling fluid turns substantially ninety degrees as the cooling fluid exits the inlet section and enters the circumferentially-extending section, wherein the cooling passageway is arranged such that the cooling fluid turns substantially ninety degrees as the cooling fluid exits the circumferentially-extending section and enters the outlet section, and wherein the circumferentially-extending section is substantially rectangular in cross-section including a width in an axial direction and a height in a radial direction greater than the width.
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Dependencies are inferred from the claim text.