Joint for connection to variable guide vane of gas turbine engine

A compressor section of a gas turbine engine, comprising:

• one or more rotor stages configured to rotate about an engine central longitudinal axis;
• one or more stator stages, the one or more stator stages including a variable pitch stator vane stage including:
• a plurality of stator vanes extending across a flowpath of the gas turbine engine;
• and
• an actuation assembly operably connected to the plurality of start stator vanes, including:
• an actuation ring extending circumferentially around the engine central longitudinal axis of the gas turbine engine;
• and
• a plurality of vane links, each vane link operably connecting a corresponding stator vane of the plurality of stator vanes to the actuation ring, a vane link of the plurality of vane links including:
• a link body;
• and
• a first link end connected the link body, the first link end including a first spherical connection to the actuation ring;
• wherein circumferential movement of the actuation ring about the engine central longitudinal axis urges rotation of the plurality of vanes about their respective vane axes;
• and
• a vane arm operably connected to a vane stem of a vane of the plurality of vanes via a vane bolt and extending from the vane stem, the vane arm secured to a second link end of the vane link, the second link end including a spherical connection to the vane arm.

A gas turbine engine, comprising:

• a combustor section;
• a turbine section driven by products of the combustion section;
• a compressor section driven by rotation of the turbine section;
• and
• a variable pitch stator vane stage disposed at at least one of the turbine section and the compressor section, the variable pitch stator vane stage, including:
• a plurality of stator vanes extending across a flowpath of the gas turbine engine;
• and
• an actuation assembly operably connected to the plurality of stator vanes, including:
• an actuation ring extending circumferentially around an engine central longitudinal axis of the gas turbine engine;
• and
• a plurality of vane links, each vane link operably connecting a corresponding stator vane of the plurality of stator vanes to the actuation ring, a vane link of the plurality of vane links including:
• a link body;
• and
• a first link end connected the link body, the first link end including a first spherical connection to the actuation ring;
• wherein circumferential movement of the actuation ring about the engine central longitudinal axis urges rotation of the plurality of vanes about their respective vane axes;
• and
• a vane arm operably connected to a vane stem of a vane of the plurality of vanes via a vane bolt and extending from the vane stem, the vane arm secured to a second link end of the vane link, the second link end including a spherical connection to the vane arm.