Patent ID: 11970278
Assignee: GENERAL ELECTRIC COMPANY
Field: Transport (Mechanical engineering)
Classification: CPC B  F  Y | IPC B  F

Claim 15:
16. An engine assembly secured to an aircraft, the engine assembly, comprising:
an aircraft engine comprising an axis of rotation, a forward frame, and an aft frame;
an engine support structure of the aircraft, the engine support structure defining a location for mounting the aircraft engine to the aircraft;
a forward engine mount connecting the forward frame of the aircraft engine to the engine support structure of the aircraft;
an aft engine-mount connecting the aft frame of the aircraft engine to the engine support structure of the aircraft; and
a thrust mount assembly, comprising:
a thrust link-lever having a first end region, a second end region separated from the first end region by a vertically oriented plane including the axis of rotation of the aircraft engine, and a fulcrum region disposed between the first end region and the second end region;
a first thrust link coupled or couplable to the first end region;
a second thrust link coupled or couplable to the second end region; and
a fulcrum body of the aft engine-mount, the thrust link-lever coupled or couplable to the fulcrum body of the aft engine-mount at a fulcrum position of the thrust link-lever,
wherein the fulcrum position of the thrust link-lever is laterally offset and/or laterally adjustable relative to the vertically oriented plane.