Inlet guide vane retention feature

A gas turbine engine comprising:

• a compressor section;
• a variable vane assembly in the compressor section, the variable vane assembly including a plurality of vanes each having an inner trunnion and an outer trunnion, wherein said inner trunnion includes a partial flange extending from said inner trunnion for a first limited circumferential extent;
• an actuator connected to said outer trunnion for causing said vane to pivot to change an angle of incidence;
• and
• a shroud comprising a forward axial half and an aft axial half, and supporting said inner trunnions in recesses, wherein said recesses include a retainer portion in the aft axial half receiving said partial flange, and said retainer portion is a recess defined by a bottom wall and a ledge and extending from a central bore for a second limited circumferential extent greater than the first circumferential extent of the partial flange, and wherein said inner trunnion can pivot relative to a central axis of said central bore when said partial flange is received in said retainer portion.

A variable vane comprising:

• a vane having an airfoil, the vane having a first end and a second end;
• a first trunnion attached to said first end of said vane, adapted to accept a force from an actuator to cause a rotational moment to be applied to said vane about a central axis;
• and
• a second trunnion attached to said second end of the vane, comprising a first portion that is substantially cylindrical and a partial flange extending from said first portion of said second trunnion for a limited circumferential extent relative to the central axis.