Patent ID: 8733693

Claim:
An aircraft engine assembly comprising: a turbojet engine comprising a fan casing, an intermediate casing located radially toward the inside with respect to the fan casing and connected to the fan casing by a plurality of structural arms, and a central casing extending along the intermediate casing toward the rear; an annular load-transfer structure surrounding the central casing and mechanically connected to the central casing by an intermediary of a mounting means, the mounting means comprising a plurality of connecting rods, the annular structure being also connected to a plurality of substantially planar structures arranged externally with respect to the annular load-transfer structure, and biasing the central casing respectively at a plurality of load application points circumferentially distributed on the annular load-transfer structure; wherein at least one connecting rod of the plurality of connecting rods is associated with a load application point from the plurality of load application points, wherein the at least one connecting rod, when viewed from the front along a longitudinal axis of the turbojet engine, is positioned tangentially with respect to the central casing, and includes an inner end connected to the central casing, and an outer end connected to the annular load-transfer structure so that a plane in which the annular load-transfer structure is located extends through the load application point from the plurality of load application points, and extends through the at least one connecting rod, wherein the connecting rods all extend in a same circumferential direction from an outer end of the connecting rods, and wherein under differential thermal expansion the annular load-transfer structure turns about the central casing while staying coaxial with the central casing.