Cooled cooling air system for a turbofan engine
US10794288B2 · kind B2 · utility
6Cited by
74References
20Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Jul 7, 2015 |
| Grant date | Oct 6, 2020 |
| Priority date | — |
| Expiry date | Oct 20, 2037 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
An exemplary gas turbine engine includes a fan bypass duct defined between a fan nacelle and core cowl of an engine core. The engine core includes a cooled cooling air system configured to receive cooling air from a primary flowpath bleed at a diffuser within the engine core and configured to provide cooled cooling air to at least one component within the engine core. The cooled cooling air system including an air-air heat exchanger.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.