Patent ID: 7559191

Claim:
A system for cooling an engine of an aircraft, wherein the engine drives a ducted fan, comprising: a first nacelle surrounding the engine; a second nacelle substantially concentrically surrounding the first nacelle; a first spinner coupled around a base of a rotor of the ducted fan; a second spinner substantially concentrically surrounding the first spinner and configured to form a duct between the first and second spinners, wherein the second spinner comprises an opening configured to allow air to flow into the duct for cooling the engine, and wherein the rotor comprises: a plurality of airfoils penetrating through the first and second spinners, wherein each of the plurality of airfoils comprises a first portion located in the duct, and a second portion located between the second spinner and a fuselage of the ducted fan, wherein the first portions of the plurality of airfoils are configured to provide cooling airflow over the engine and structural support for the second portions, and wherein the second portions of the plurality of airfoils are configured to provide thrust for the aircraft.