Patent ID: 6527224
Filing Date: 2003-03-04
Classification: B64C,B64D,F02C,F02K,Y02T

Abstract:
An engine inlet assembly for a jet propulsion engine of a blended wing-body aircraft, said jet propulsion engine being mounted upon a substantially uninterrupted lifting member of said blended wing-body aircraft, said jet propulsion engine having a turbine section and a bypass fan section, said bypass fan section providing cold flow thrust to said jet propulsion engine, said engine inlet assembly comprising:a first air inlet being positioned generally within a boundary layer flowing around said substantially uninterrupted lifting member of the aircraft, said first air inlet being operable to scavenge said boundary layer to maintain the flow of said boundary layer over said substantially uninterrupted lifting member to reduce drag; a first passage fluidly connectable between said first air inlet and an inlet to the bypass fan section of the jet propulsion engine; a second air inlet being positioned generally outside of said boundary layer; and a second passage fluidly connectable between said second air inlet and an inlet to the turbine section of the jet propulsion engine, said second passage being separate from said first passage.