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US 2016/0237903 A1Published application
High Pressure Compressor Rotor Thermal Conditioning Using Conditioned Compressor Air
AssigneeUnited Technologies Corporation
InventorsPaul J. Hiester, Matthew P. Forcier
Life of this patent
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Abstract
A gas turbine engine comprises a compressor including a disk and a blade. A turbine rotor has a disk and a blade. Turbine conditioning air is supplied to the turbine rotor. The turbine conditioning air passes across the disk of the compressor to condition the disk. A method of operating a gas turbine engine is also disclosed.
Claims20
A gas turbine engine comprising:
- a compressor including a disk and a blade;
- a turbine rotor having a disk and a blade;
- turbine conditioning air supplied to said turbine rotor;
- and
- said turbine conditioning air passing across said disk of said compressor to condition said disk.
2 more elements
A method of operating a gas turbine engine comprising the steps of:
- supplying a turbine conditioning air to a turbine rotor;
- and
- passing said turbine conditioning air across a disk of a compressor to condition the disk of the compressor.
Dependencies are inferred from the claim text.