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US 2020/0049013 A1Published application
Geared gas turbine engine
AssigneeUnited Technologies Corporation
InventorsChristopher J. Knortz, William W. Frank, Erica J. Harvie, Conor Lee
Life of this patent
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Abstract
A rotor assembly includes a plurality of rotor disks that each have a rim portion. The plurality of rotor disks includes a first rotor disk and at least one first bleed air passage that extends through a forward rim portion of the first rotor disk. At least one second bleed air passage that extends through an aft rim portion of the first rotor disk.
Claims20
A rotor assembly comprising:
- a plurality of rotor disks each having a rim portion, wherein the plurality of rotor disks includes a first rotor disk;
- and
- at least one first bleed air passage extending through a forward rim portion of the first rotor disk and at least one second bleed air passage extending through an aft rim portion of the first rotor disk.
A gas turbine engine comprising:
- a compressor section connected to rotate with a turbine section by a shaft, wherein the compressor section includes:
- a plurality of rotor disks each having a rim portion, wherein the plurality of rotor disks includes a first rotor disk;
- and
- at least one first bleed air passage extending through a forward rim portion of the first rotor disk and at least one second bleed air passage extending through an aft rim portion of the first rotor disk.
1 more element
A method of operating a gas turbine engine comprising:
- rotating a plurality of rotor disks, wherein the plurality of rotor disks includes a first rotor disk;
- and
- bleeding core air flow of the gas turbine engine through at least one first bleed air passage extending through a forward rim portion of the first rotor disk and bleeding the core air flow through at least one second bleed air passage extending through an aft rim portion of the first rotor disk.
Dependencies are inferred from the claim text.