초록 ▼

A combination lift and thrust device for increasing the performance of an aircraft by simultaneously reducing drag and augmenting the thrust of a turbojet engine carried within the device. The device comprises a wing of generally airfoil shape having numerous geometrically spaced apertures penetrati

A combination lift and thrust device for increasing the performance of an aircraft by simultaneously reducing drag and augmenting the thrust of a turbojet engine carried within the device. The device comprises a wing of generally airfoil shape having numerous geometrically spaced apertures penetrating its surface, a turbojet engine carried within the wing, an elongated exhaust plenum attached to the turbojet having a number of strategically positioned exhaust nozzles, and a mixing chamber having a forward opening and a rear nozzle also carried within the wing. The mixing chamber forward opening is cooperatively associated with the exhaust nozzles to form an ejector drawing air through the apertures in the wing into the forward opening, mixing the air with the exhaust gases from the turbojet to provide thrust augmentation, and exhausting the air and gas mixture from the rear nozzle of the mixing chamber. The air drawn through the apertures in the wing surface reduces the turbulent boundary layer on the wing thus reducing the aerodynamic drag of the wing.

대표청구항 ▼

An improved combination lift and thrust device for use in aircraft application, comprising: (a) a wing of general airfoil shape for providing lift as the device is moved forwardly through the air, said wing including a forward opening and a membrane having a plurality of spaced apart apertures there

An improved combination lift and thrust device for use in aircraft application, comprising: (a) a wing of general airfoil shape for providing lift as the device is moved forwardly through the air, said wing including a forward opening and a membrane having a plurality of spaced apart apertures therethrough so constructed and arranged as to permit a flow of substantial amounts of air through said membrane; (b) a turbojet engine carried within said wing, said engine having an exhaust duct for the exhaustion of the gases of combustion from said engine and an inlet duct communicating with said forward opening in said wing; (c) an elongated exhaust plenum, including a hollow body portion diverging horizontally and converging vertically from the forward extremity to the rearward extremity of said hollow body portion, said hollow body portion interconnected proximate the forward extremity thereof with said engine exhaust duct and being provided proximate the rearward extremity thereof with a closure plate having a plurality of apertures and a plurality of spaced apart exhaust nozzles mounted within the apertures of said closure plate for receiving the gases of combustion from said engine and rearwardly ejecting said gases at high velocity imparting maximum turbulence to the flow of said gases; and (d) a mixing chamber carried within said wing proximate said exhaust plenum, said mixing chamber having a forward opening and a rearward opening, said forward opening being adapted to receive the gases of combustion being ejected by said exhaust nozzles and at the same time being adapted to receive and intermix with said gases of combustion the air flowing through said apertures in said membrane of said wing whereby the close proximity of adjacent turbulent gas jets formed by said plurality of nozzles increases efficiency of entrainment and mixing of said gases of combustion and air in the short length of the mixing chamber increasing substantially the efficiency of the ejector formed by said mixing chamber.