Patent ID: 8141337

Claim:
A bypass turbine engine for an aircraft, said turbine engine comprising: a hollow nacelle having a longitudinal axis an air inlet at a front portion of the hollow nacelle and an air outlet at a rear portion of the hollow nacelle; a central hot-stream generator, positioned axially in said nacelle; a fan, which generates a cold stream flow, positioned axially in said nacelle and forward of said central hot-stream generator; an outer fairing and an inner fairing internal to said nacelle, wherein said an inner fairing surrounds said central hot-stream generator, and said outer and inner fairings are positioned so as to define between the outer and inner fairings a fan duct of annular cross section for said cold stream flow, with said inner fairing and said central hot-stream generator being positioned so as to define an intermediate chamber of annular cross section that surrounds the central hot-stream generator internal to said inner fairing for said cold stream flow, with said inner fairing having a rear part at the rear portion of the hollow nacelle; and a precooler comprising an inlet for a current of hot air bled from said central hot-stream generator and an outlet for a current of hot air cooled from said cold stream flow, wherein said precooler is positioned inside at least a portion of said rear part of the inner fairing around said longitudinal axis, and in the intermediate chamber so as to be in thermal contact with and cooled by said cold stream flow through the intermediate chamber.