Engine assembly for an aircraft comprising attachments for engines offset below on the fan frame

摘要

An aircraft engine assembly including an attachment mechanism of a turbojet onto a rigid structure of a mounting strut, including a first, second, and third forward engine attachment for taking up thrust loads brought onto the fan frame, and arranged such that the third attachment passes through a first diametrical plane of the turbojet, the first and second attachments being disposed on one side and another of the first plane. The first and second forward engine attachments are respectively brought to the fan frame at two points, situated beyond the second diametrical plane of the turbojet, orthogonal to the first diametrical plane, with respect to the third attachment.

主权项

1. An aircraft engine assembly comprising:
a turbojet comprising a fan frame, an intermediate casing radially situated to an interior with respect to the fan frame and linked to the fan frame by a plurality of structural arms, and a central casing extending the intermediate casing towards a rear; and a mounting strut comprising a rigid structure comprising a longitudinal box and two lateral boxes integrated with the longitudinal box and arranged on two sides of the longitudinal box, the mounting strut further comprising a mount to mount the turbojet onto the rigid structure, the mount comprising first, second, and third forward engine attachments to take up thrust loads brought to the fan frame, and arranged such that the third forward engine attachment passes through a first diametrical plane of the turbojet, the first and second forward engine attachments, respectively carried on the two lateral boxes, being arranged on one side and another in the first diametrical plane, wherein the first and second forward engine attachments are respectively brought to the fan frame at only two points, which are situated beyond a second diametrical plane of the turbojet, orthogonal to the first diametrical plane, with respect to the third forward engine attachment, such that the two lateral boxes include ends that carry the first and second forward engine attachments with the ends extending beyond the second diametrical plane of the turbojet, and the lateral boxes each include a structural portion including a curved contour and a structural portion including a straight contour, and the structural portion including the straight contour carries one of the first and second forward engine attachments and extends beyond the second diametrical plane of the turbojet.