Patent ID: 8250852

Claim:
A bypass turbine engine for an aircraft, comprising: a hollow nacelle of longitudinal axis provided, at the front, with an air inlet and, at the rear, with an air outlet; a central hot-stream generator, positioned axially in said nacelle; a fan positioned axially 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 delimiting a fan duct of annular cross section for said cold stream and said inner fairing delimiting with said central generator an intermediate chamber of annular cross section surrounding said central generator and provided with at least one rear orifice at the periphery of said hot stream; and a precooler comprising an inlet for a current of hot air bled from said central generator and an outlet for a current of cooled hot air generated using said cold stream, wherein: said precooler is positioned inside said intermediate chamber in thermal contact with the rear part of the inner fairing, forming an intermediate passage between said precooler and said central generator; and forward of said precooler, there is at least one air intake passing through said inner fairing and bleeding from said cold stream, a current of cooling air able at least partially to cool said current of hot air entering said precooler.