Patent ID: 7926261

Claim:
A bypass turbine engine for an aircraft, said turbine engine being suspended from a ycing of the aircraft via a suspension pylon and comprising: a hollow nacelle of longitudinal axis provided with an air inlet at a front and with a jet pipe at the rear; a central hot-stream generator, positioned axially in said nacelle; a fan positioned in said nacelle forward of said central generator and able to generate a cold stream for said turbine engine; an outer fairing borne internally by said nacelle and an inner fairing surrounding said central generator, said outer and inner fairings between them forming a fan duct of annular cross section for said cold stream, said inner fairing and said central generator delimiting a chamber of annular cross section surrounding said central generator; a pre-cooler receiving a current of hot air bled from said central generator and a current of cold air bled from said cold stream so as to generate a current of cooled hot air intended for performing functions on board the aircraft, said pre-cooler at a same time generating a current of heated cold air; and at least one discharge orifice for discharging said current of heated cold air, said discharge orifice being made in said inner fairing and facing upward at least approximately toward said wing, wherein said bypass turbine engine comprises at least one discharge pipe positioned in said chamber and connected to said pre-cooler for conducting said current of heated cold air to said at least one discharge orifice and wherein said at least one discharge orifice is positioned behind said jet pipe, such that said heated cold air is discharged into said cold stream at the exit from said turbine engine.