Patent ID: 8646725

Claim:
An engine assembly for an aircraft, comprising: a dual-flow turbomachine; and an attachment strut to mount the turbomachine configured to be connected to an element of the aircraft, wherein the turbomachine includes a fan casing and an intermediate casing positioned downstream of the fan casing and including a hub supporting structural arms, wherein the attachment strut includes a primary structure to transmit forces, wherein the turbomachine further includes a first structural case extending downstream of the hub of the intermediate casing, wherein the first structural case contributes to an internal radial delimitation of a passage for a secondary flow of the turbomachine, wherein the primary structure of the attachment strut includes a second structural case, assembled on the first structural case, and positioned directly downstream of the first structural case, to also contribute to the internal radial delimitation of the passage for the secondary flow, wherein the primary structure of the attachment strut also includes an offset structure positioned in the passage for the secondary flow, a portion of the offset structure extending downstream with respect to a downstream end of the second structural case, and the portion of the offset structure is configured to connect the second structural case to the aircraft element, and wherein the second structural case includes a thrust reversal system.