|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||060/728; 060/226.1; 060/785|
|발명자 / 주소|
|출원인 / 주소|
|대리인 / 주소||
|인용정보||피인용 횟수 : 17 인용 특허 : 15|
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 by...
We claim: 1. A cooling system for an aircraft comprising: an engine nacelle including an airflow inlet; an engine housed in the engine nacelle in flow communication with the airflow inlet; a bypass duct extending between the engine nacelle and the engine in flow communication with the airflow inlet, the bypass duct including an outer wall having an opening formed therein; and a heat exchanger integrated with the engine and disposed outside of the bypass duct over the opening of the bypass duct outer wall between the bypass duct outer wall and the engine...