Thermal management system for a gas turbine engine
US7475549B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Aug 3, 2005 |
| Grant date | Jan 13, 2009 |
| Priority date | — |
| Expiry date | Feb 10, 2027 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A thermal management system for a gas turbine engine includes a cooling airflow which enters through an air filter portion of a forward cover for filtration of particulate which may result in FOD to a rotational system of the engine. Filtered cooling airflow flows along a rotor shaft over and through a forward bearing, over and through a permanent magnet generator, then over and through an aft bearing to provide thermal management. Commensurate therewith, the cooling airflow atomizes and communicates a lubricant to the bearings. From the aft bearing, the cooling airflow merges with a primary airflow path from an intake which generally surrounds the forward cover.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.