Thermal management system for a gas turbine engine
AssigneeUnited Technologies Corporation
InventorsDaniel Benjamin, Daniel Carminati, David S. Jang
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Abstract
A thermal management system for a gas turbine engine includes a high pressure compressor rotor having a plurality of disks and a shaft; at least one forward cavity formed between a rim of at least one of the disks and the shaft and at least one aft cavity formed between a rim of at least one other of the disks and the shaft; a first flow of cooling air in the at least one forward cavity; and a second flow of cooling air in the at least one aft cavity.
Claims32
A thermal management system for a gas turbine engine comprising:
- means for delivering a first stream of cooling air to at least one forward cavity for controlling disk temperature and shaft temperature;
- and
- means for delivering a second stream of cooling air to at least one aft cavity for providing disk web cooling.
A process for thermally managing a gas turbine engine which comprises the steps of:
- providing a compressor rotor having a plurality of disks and a first shaft, which engine section has at least one forward cavity formed between a rim of at least one of said disks and said first shaft and at least one aft cavity formed between a rim of at least one other of said disks and said first shaft;
- creating a first flow of cooling air in said at least one forward cavity;
- and
- creating a second flow of cooling air in said at least one aft cavity.
Dependencies are inferred from the claim text.