Patent ID: 7360990

Claim:
A method for assembling a variable vane assembly for a gas turbine engine including a casing and an inner shroud, said method comprising: providing at least one variable vane including a radially inner spindle that has a substantially circular cross-sectional shape; coupling the variable vane radially between the casing and the inner shroud such that the radially inner spindle is rotatably coupled within an opening extending through the inner shroud, wherein the opening has a first recessed portion, a second recessed portion and a third opening portion that extends from the second recessed portion to the first recessed portion wherein the third opening portion has a non-circular cross-sectional profile defined by a continuous wall, wherein the first recessed portion, the second recessed portion, and the third opening portion extend along an axis parallel to an axis of the variable vane; and slidably coupling a bushing into the shroud opening such that the bushing receives a portion of the radially inner spindle therein, wherein the bushing includes a portion having non-circular cross-sectional shape that is inserted through the second portion opening and is sized to be received within the third opening portion, and a base portion having a circular cross-sectional shape sized to be received within the second recessed portion, such that an outer end surface of the base portion is substantially flush with said shroud radially inner surface.