Patent ID: 11939070
Assignee: GENERAL ELECTRIC COMPANY
Field: Transport (Mechanical engineering)
Classification: CPC B | IPC B

Claim 10:
11. An engine assembly secured to an aircraft, the engine assembly, comprising:
an aircraft engine comprising an engine frame that has a forward frame portion and an aft frame portion;
an engine support structure that defines a location for mounting the aircraft engine to an aircraft;
a forward link connected to the forward frame portion of the engine frame and to the engine support structure of the aircraft, wherein force vectors extending from the forward link intersect at a forward focal point;
an aft link connected to the aft frame portion of the engine frame and to the engine support structure of the aircraft, wherein force vectors extending from the aft link intersect at an aft focal point; and
an actuator connected to the engine support structure and the forward link, or to the engine support structure and the aft link, or to the engine support structure and the forward frame portion of the engine frame, or to the engine support structure and the aft frame portion of the engine frame;
wherein the actuator, when actuated, changes an inclination angle θ of at least one of the forward link and/or the aft link from a first inclination angle θ to a second inclination angle θ such that a location of at least one of the forward focal point or the aft focal point is moved, and the engine frame shifts forward or aft with respect to the engine support structure such that the engine frame is substantially horizontal with respect to the engine support structure at the first inclination angle θ and at the second inclination angle θ.