Patent attributes
Bypass turbojet engine comprising a fan casing (5) at the front and an exhaust casing at the rear, said turbojet engine further comprising a cold stream duct (7) which comprises an annular rear end connected to the exhaust casing and on which is positioned at least one attachment point (4) able to transmit the load from the exhaust casing to the structure of an aircraft, characterized in that a plurality of attachment points (4g, 4d) is positioned on the circumference of said annular rear end of the cold stream duct (7), said plurality of attachment points comprising either two points (4g, 4d) that are diametrically opposed on said circumference or at least three points that form a polygon through which the axis of symmetry of the cold stream duct (7) passes, and in that the turbojet engine is equipped with a rear suspension hoop (8) fixed to said attachment points and able to be fixed to the structure of the aircraft.
