COOLING SYSTEMS FOR USE ON AIRCRAFT

摘要

Cooling systems (102) for an aircraft (100) are provided. In an embodiment, a system includes an engine nacelle (103), an engine (101), a bypass duct (119), and a heat exchanger (136). The engine nacelle (103) includes an airflow inlet. The engine (101) is housed in the engine nacelle (103) in flow communication with the airflow inlet. The bypass duct (119) extends between the engine nacelle (103) and the engine (101) is in flow communication with the airflow inlet. The bypass duct (119) includes an outer wall (123) and an opening (124) formed therein. The heat exchanger (136) is integrated with the engine (101) and is disposed over the opening (124) of the bypass duct outer wall (123) between the bypass duct outer wall (123) and the engine nacelle (103).