Cooling systems for use on aircraft
US7856824B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Jun 25, 2007 |
| Grant date | Dec 28, 2010 |
| Priority date | — |
| Expiry date | Aug 21, 2029 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
Cooling systems for an aircraft are provided. In an embodiment, a system includes an engine nacelle, an engine, a bypass duct, and a heat exchanger. The engine nacelle includes an airflow inlet. The engine is housed in the engine nacelle in flow communication with the airflow inlet. The bypass duct extends between the engine nacelle and the engine is in flow communication with the airflow inlet. The bypass duct includes an outer wall and an opening formed therein. The heat exchanger is integrated with the engine and is disposed over the opening of the bypass duct outer wall between the bypass duct outer wall and the engine nacelle.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.