Patent ID: 11970956
Assignee: GENERAL ELECTRIC COMPANY
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F  B | IPC F

Claim 16:
17. A pitch change mechanism for a gas turbine engine having a turbomachine and a fan, the fan including a plurality of fan blades, the pitch change mechanism comprising:
a plurality of linkages, the plurality of linkages including a first linkage configured to be coupled to a first fan blade of the plurality of fan blades and a second linkage configured to be coupled to a second fan blade of the plurality of fan blades; and
a non-uniform blade actuator system operable with one or more of the plurality of linkages to control a pitch of the first fan blade relative to a pitch of the second fan blade, the non-uniform blade actuator system including an interface surface having a non-uniform geometry, the interface surface configured to slidably engage with the plurality of linkages.