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A method enables a variable vane assembly for a gas turbine engine including a casing and an inner shroud to be assembled. The method comprises providing at least one variable vane including a radially inner spindle that has a substantially circular cross-sectional shape, and coupling the variable v

A method enables a variable vane assembly for a gas turbine engine including a casing and an inner shroud to be assembled. The method comprises providing at least one variable vane including a radially inner spindle that has a substantially circular cross-sectional shape, and 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 non-circular cross-sectional profile.

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What is claimed is: 1. 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

What is claimed is: 1. 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. 2. A method in accordance with claim 1 wherein the bushing includes a substantially circular opening extending at least partially therethrough and has a non-circular cross-sectional shape defined at its perimeter by a continuous outer surface of the bushing. 3. A method in accordance with claim 1 wherein slidably coupling a bushing into the shroud opening further comprises slidably coupling the bushing in the shroud opening to facilitate reducing wear of the variable vane. 4. A method in accordance with claim 1 further comprising inserting a substantially cylindrical wear sleeve between the radially inner spindle and the bushing. 5. A method in accordance with claim 1 further comprising slidably coupling a substantially cylindrical wear sleeve to the radially inner spindle to facilitate reducing wear of the radially inner spindle. 6. A variable vane assembly for a gas turbine engine including a casing, said variable vane assembly comprising: a variable vane comprising a radially inner spindle and a radially outer spindle, said radially inner and outer spindles configured to rotatably couple said vane within the gas turbine engine, said radially inner spindle comprises a first cross-sectional shape defined by an external surface of said radially inner spindle; an inner shroud comprising a radially outer surface, a radially inner surface, and at least one opening extending between said radially outer and inner surfaces, said radially inner spindle sized for insertion through said opening for rotatably coupling said variable vane to said inner shroud, said opening comprises a first recessed portion, a second recessed portion and a third opening portion that extends from said second recessed portion to said first recessed portion, said third opening portion has a non-circular cross-sectional profile defined by a continuous wall that extends from said first recessed portion to said second recessed portion, wherein said first recessed portion, said second recessed portion and said second cross-sectional profile extend along an axis parallel to an axis of said variable vane; and a bushing comprising a non-circular cross-sectional shape portion sized to be received within a portion of said opening, 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, and an opening sized to receive a portion of said radially inner spindle therein. 7. A variable vane assembly in accordance with claim 6 wherein said bushing is sized for insertion within said inner shroud opening such that said bushing extends circumferentially around said radially inner spindle within said opening. 8. A variable vane assembly in accordance with claim 6 wherein said bushing is configured to facilitate reducing wear of said variable vane. 9. A variable vane assembly in accordance with claim 6 wherein said bushing comprises an outer surface, an inner surface, and an opening extending therethrough, said opening defined by said bushing inner surface and having a cross-sectional shape that is different than a cross-sectional shape of said bushing as defined by said bushing outer surface. 10. A variable vane assembly in accordance with claim 9 wherein said bushing outer surface cross-sectional shape is substantially similar to that of said inner shroud opening second cross-sectional profile such that said bushing is slidably coupled within said inner shroud opening. 11. A variable vane assembly in accordance with claim 9 wherein said bushing opening cross-sectional shape is substantially similar to that of said inner spindle first cross-sectional profile. 12. A variable vane assembly in accordance with claim 6 further comprising a cylindrical wear sleeve slidably coupled to and extending circumferentially around said radially inner spindle. 13. A variable vane assembly in accordance with claim 12 wherein said wear sleeve is hollow and has an outer diameter that is smaller than a diameter of said bushing opening, and an inner diameter that is larger than a diameter of said radially inner spindle. 14. A gas turbine engine comprising: a rotor comprising a rotor shaft and a plurality of rows of rotor blades; a casing surrounding each of said plurality of rows of rotor blades; a variable vane assembly comprising at least one row of circumferentially-spaced variable vanes and a retainer assembly, said at least one row of variable vanes rotatably coupled to said casing and extending between an adjacent pair of said plurality of rows of rotor blades, each said variable vane comprising a radially inner spindle configured to rotatably couple to an inner shroud within said gas turbine engine, each said radially inner spindle comprises a first cross-sectional shape defined by an external surface of said radially inner spindle, said shroud comprising a radially outer surface, a radially inner surface, and at least one opening extending therebetween, said opening comprising a first recessed portion, a second recessed portion and a third opening portion that extends from said second recessed portion to said first recessed portion, said third opening portion has a non-circular cross-sectional profile defined by a continuous wall that extends from said first recessed portion to said second recessed portion, wherein said first recessed portion, said second recessed portion, and said second cross-sectional profile extend along an axis parallel to an axis of said variable vane; and a bushing comprising a non-circular cross-sectional shape portion sized to be received within a portion of said opening, 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, and an opening sized to receive a portion of said radially inner spindle therein. 15. A gas turbine engine in accordance with claim 14 wherein said inner shroud extends substantially circumferentially between each adjacent pair of said plurality of rows of rotor blades, and wherein said bushing is sized for insertion within said inner shroud opening to facilitate reducing wear of said variable vane. 16. A gas turbine engine in accordance with claim 14 wherein said bushing extends circumferentially around said radially inner spindle within said inner shroud opening. 17. A gas turbine engine in accordance with claim 14 wherein said bushing comprises an outer surface, an inner surface, and an opening extending therebetween, said bushing opening has a cross-sectional shape defined by said bushing inner surface that is different than a cross-sectional shape defined by said bushing outer surface. 18. A gas turbine engine in accordance with claim 14 wherein said bushing outer cross-sectional shape is substantially similar to that of said inner shroud opening cross-sectional shape such that said bushing is slidably coupled within said inner shroud opening. 19. A gas turbine engine in accordance with claim 14 wherein said variable vane assembly further comprises a wear sleeve slidably coupled to said radially inner spindle to facilitate extending a useful life of said variable vane assembly. 20. A gas turbine engine in accordance with claim 19 wherein said variable vane assembly wear sleeve extends circumferentially around said radially inner spindle and has an outer diameter that is smaller than a diameter of said bushing opening.