Patent attributes
A system for cooling a ducted fan aircraft engine includes a first nacelle surrounding the engine and a second nacelle substantially concentrically surrounding the first nacelle. The system includes a first spinner coupled around a base of a rotor of the ducted fan and a second spinner substantially concentrically surrounding the first spinner and forming a duct between first and second spinners. The second spinner includes an opening to allow air to flow into the duct. The rotor includes a plurality of airfoils penetrating through the first and second spinners. Each of the airfoils includes a first portion located in the duct, and a second portion located between the second spinner and a fuselage of the ducted fan. The first portions of the airfoils provide cooling airflow over the engine and structural support for the second portions. The second portions of the airfoils provide thrust for the aircraft.
