Variable pitch fan of a gas turbine engine
AssigneeGE Avio S.r.l.
InventorsPaolo Altamura, Giulio Zagato
Life of this patent
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Abstract
A gas turbine engine includes 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 to control a pitch of the plurality of fan blades. The pitch change mechanism imparts a torque to each fan blade of the plurality of fan blades via first and second forces imparted in opposite directions to each fan blade of the plurality of fan blades.
Claims18
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 to control a pitch of the plurality of fan blades, the pitch change mechanism imparting a torque to each fan blade of the plurality of fan blades via first and second forces imparted in opposite directions to each fan blade of the plurality of fan blades;
- wherein the pitch change mechanism comprises a forward unison ring and an aft unison ring;
- wherein the pitch change mechanism further comprises a plurality of forward racks coupled to the forward unison ring and a plurality of aft racks coupled to the aft unison ring.
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 aft racks, each aft rack of the plurality of aft racks coupled to a respective fan blade of the plurality of fan blades;
- a plurality of forward racks, each forward rack of the plurality of forward racks coupled to the respective fan blade of the plurality of fan blades;
- and
- an actuator system operably coupled with the plurality of aft racks and the plurality of forward racks to control a pitch of the plurality of fan blades.
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 trunnion mechanisms rotatably coupling each fan blade of the plurality of fan blades to a disk;
- a pinion coupled to each trunnion mechanism;
- a plurality of aft racks, each aft rack of the plurality of aft racks operably coupled with the pinion of a respective trunnion mechanism;
- a plurality of forward racks, each forward rack of the plurality of forward racks operably coupled with the pinion of the respective trunnion mechanism;
- and
- an actuator system operable with the plurality of aft racks and the plurality of forward racks to impart a torque to the pinion of the respective trunnion mechanism.
Dependencies are inferred from the claim text.