Patent ID: 7856824

Claim:
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 nacelle and having a wall that is integrally formed with the bypass duct outer wall, the heat exchanger includes a bypass flow path air inlet, an engine air inlet, a first outlet, and a second outlet, the bypass flow path air inlet providing flow communication between the bypass flow path and the first outlet, the engine air inlet providing flow communication between the engine and the second outlet.