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

Claim 0:
1. A gas turbine engine comprising:
a turbomachine comprising a compressor section, a combustion section, and a turbine section arranged in serial flow order;
a fan defining a fan axis and comprising a plurality of fan blades rotatable about the fan axis; and
a pitch change mechanism operable with the plurality of fan blades, the pitch change mechanism comprising
a plurality of linkages, the plurality of linkages including a first linkage coupled to a first fan blade of the plurality of fan blades and a second linkage 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.