Patent ID: 11970974
Assignee: RTX CORPORATION
Field: Transport (Mechanical engineering)
Classification: CPC B  F  Y | IPC B  F

Claim 0:
1. An aircraft comprising: a fuselage and a pair of wings extending laterally outwardly of said fuselage, said wings including a relatively straight portion between said fuselage and a gas turbine engine, and a swept portion laterally outwardly of said gas turbine engine relative to said fuselage, the relatively straight portion is closer to being perpendicular to a fuselage centerline of the aircraft compared to the swept portion; an engine mount structure attaching said gas turbine engine to said relatively straight portion, and vertically above said wings, said gas turbine engine having a core engine including a compressor section, a combustor section and a turbine section mounted within a core engine housing; a fan, said fan, said compressor section and said turbine section rotating about an axis of rotation; an outer nacelle surrounding said fan, and being spaced from said core engine housing to define a bypass duct, said fan delivering air into said bypass duct and into said core engine housing; said nacelle being formed with camber so as to be curved in a first plane defined parallel to the horizontal and away from said axis of rotation in a first lateral direction, and said engine mount structure extending from said nacelle at an angle that is non-parallel and non-perpendicular to said first plane, and having a component in a lateral direction that is opposed to said first lateral direction; and a shape of the nacelle and its camber improving a wing leading edge suction terminating in a shock wave in a forward inboard portion of the wings, and at the relatively straight section.