Cooling system for an aero gas turbine engine
US8833053B2 · kind B2 · utility
14Cited by
8References
9Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Feb 12, 2010 |
| Grant date | Sep 16, 2014 |
| Priority date | — |
| Expiry date | Sep 20, 2032 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2300/505
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A cooling system is provided for an aero gas turbine engine. The system has a duct which diverts a portion of a bypass air stream of the engine. A heat exchanger located in the duct receives cooling air for cooling components of the engine. The cooling air is cooled in the heat exchanger by the diverted bypass air stream. After cooling the cooling air, the spent diverted air stream is routed to a tail cone located at the exit of the engine and ejected through a nozzle at the tail cone.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.