Levered counterweight feathering system

A counterweight assembly for use in a gas turbine engine, the counterweight assembly comprising:

• a link arm configured to couple with a pitch change mechanism of the gas turbine engine, a trunnion of a fan assembly of the gas turbine engine, or both, wherein the link arm is configured to drive rotation of the trunnion when coupled to the pitch change mechanism, the trunnion, or both;
• a lever arm connected to the link arm;
• a hinge pivotably connected to the lever arm, wherein the lever arm is disposed to rotate about a connection point of the lever arm and the hinge;
• and
• a counterweight mounted to the lever arm at a location spaced from the hinge, wherein the counterweight is configured to move in response to a change in centrifugal load applied to the counterweight during operation of the gas turbine engine, wherein the counterweight travels at least partially along a radial direction of the gas turbine engine.

A gas turbine engine defining an axial direction and a radial direction, the gas turbine engine comprising:

• a compressor section;
• a combustion section connected to and disposed downstream from the compressor section;
• a turbine section connected to and disposed downstream from the combustion section, wherein the compressor section, the combustion section, and the turbine section define a core turbine engine;
• and
• a fan assembly connected to and disposed upstream from the compressor section, wherein the fan assembly comprises:
• a fan disk configured to rotate about the axial centerline of the gas turbine engine when installed in the gas turbine engine;
• a trunnion mounted to the fan disk;
• an actuation device operably coupled to the trunnion;
• a fan blade defining a pitch axis and rotatably attached to the fan disk about the pitch axis through the trunnion;
• and
• a counterweight assembly comprising:
• a link arm connected to the trunnion, the actuation device, or both, wherein the link arm is configured to drive rotation of the trunnion relative to the fan disk;
• a lever arm connected to the link arm;
• a hinge pivotably connected to the lever arm, wherein the lever arm is disposed to rotate about a connection point of the lever arm and the hinge;
• and
• a counterweight mounted to the lever arm at a location spaced from the hinge, wherein the counterweight travels at least partially along the radial direction of the gas turbine engine.