Patent ID: 7677493

Claim:
An engine assembly for an aircraft, comprising: an engine configured to produce thrust along a longitudinal axis of the engine, the engine including a fan casing configured to enclose a fan of the engine, a central casing configured to enclose a combustor of the engine, and an ejection casing configured to enclose a low-pressure turbine of the engine; a rigid structure includes a main box and a fork, the fork having a base and two branches, said base being fixed to the main box and a free end of each of the two branches supporting one of two aft half-fasteners, and the fork is configured to hold the engine solely through the two aft half-fasteners; and a mounting structure configured to mount the engine onto said rigid structure, said mounting structure including a forward fastener configured to fasten the rigid structure to the engine at the fan casing, said fastener is configured to resist forces applied along a vertical direction Z and along a transverse direction Y, and said forward fastener is configured to allow the engine to move along a longitudinal direction X without substantial resistance, and two aft half-fasteners, each of the two aft half-fasteners being configured to resist at least forces applied along the longitudinal axis of the engine, said two aft half-fasteners are arranged so that a horizontal plane passing through said longitudinal axis of the engine passes through each of said two aft half-fasteners, and the two aft half-fasteners are connected to the engine at an aft end of the central casing before a junction with the ejection casing, wherein the junction between the ejection casing and the central casing is disposed at a longitudinal position between the combustor of the engine and the low-pressure turbine.