Engine assembly for an aircraft the engine attachment strut of which includes a structural case forming an internal radial delimitation of the secondary flow
An engine assembly for an aircraft including a dual-flow turbomachine and an attachment strut. The turbomachine includes a structural case extending downstream of the hub of an intermediate casing, the case contributing to the internal radial delimitation of a passage for a secondary flow of the turbomachine. Also, the primary structure includes a structural case, assembled on the structural case and positioned directly downstream of the structural case such that it also contributes to the internal radial delimitation of the passage for the secondary flow. The primary structure also includes an offset structure positioned in the passage, and configured to connect the case to an element of the aircraft. The structural case also includes a thrust reversal system.
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