Thermal management system for a gas turbine engine
US9234463B2 · kind B2 · utility
10Cited by
13References
19Claims
0Family size
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Key dates
| Filing date | Apr 24, 2012 |
| Grant date | Jan 12, 2016 |
| Priority date | — |
| Expiry date | Jun 5, 2034 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF04D29/321
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
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 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.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.