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A method for assembling a turbine engine to facilitate reducing an operating temperature of a lubrication fluid during engine operation, the gas turbine engine including a fan assembly, a booster downstream from the fan assembly, and a splitter circumscribing the booster. The method includes couplin

A method for assembling a turbine engine to facilitate reducing an operating temperature of a lubrication fluid during engine operation, the gas turbine engine including a fan assembly, a booster downstream from the fan assembly, and a splitter circumscribing the booster. The method includes coupling a radially inner wall and a radially outer wall at a leading edge to form a splitter body, and coupling an inner support structure within the splitter body such that a cooling circuit is defined between at least a portion of the inner support structure and the inner and outer walls, said cooling circuit configured to circulate lubrication fluid therethrough such that as a temperature of the lubrication fluid is reduced and a temperature of at least a portion of the inner and outer walls is increased.

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1. A method for assembling a gas turbine engine including a nacelle and a core engine disposed within the nacelle to define a core engine flow path through the core engine and a bypass duct between the core engine and the nacelle, said method comprising: forming a splitter that defines a cooling cir

1. A method for assembling a gas turbine engine including a nacelle and a core engine disposed within the nacelle to define a core engine flow path through the core engine and a bypass duct between the core engine and the nacelle, said method comprising: forming a splitter that defines a cooling circuit;coupling the splitter to the core engine such that the splitter is configured to split a flow of air between the bypass duct and the core engine flow path, the cooling circuit configured to circulate lubrication fluid through the splitter such that a temperature of the lubrication fluid is reduced and a temperature of the splitter is increased; andproviding a booster compressor of the gas turbine engine with at least one substantially hollow stator vane configured to receive lubrication fluid channeled from the splitter via forced circulation induced by at least one fluid pumping device. 2. A method in accordance with claim 1 wherein forming a splitter comprises: coupling a radially inner wall and a radially outer wall to form a splitter body;coupling a radially inner portion to a radially outer portion at a leading edge to form a substantially U-shaped central portion; andcoupling a plurality of longitudinal structural members between the central portion and the inner wall such that a first flowpath portion is defined between the central portion and the inner wall. 3. A method in accordance with claim 1 wherein forming a splitter comprises: coupling a radially inner wall and a radially outer wall to form a splitter body;coupling a radially inner portion to a radially outer portion at a leading edge to form a substantially U-shaped central portion; andcoupling a plurality of radial structural members between the central portion and the outer wall such that a second flowpath portion is defined between the central portion and the outer wall. 4. A method in accordance with claim 3 wherein coupling a radially inner portion to a radially outer portion at a leading edge further comprises: coupling the radially inner portion including a plurality of steps to the radially outer portion to form the substantially U-shaped central portion; andcoupling a plurality of substantially L-shaped radial structural members between the stepped inner portion and the outer wall. 5. A method in accordance with claim 3 further comprising coupling a plurality of stiffeners to an external surface of the outer wall, each stiffener having a profile that is configured to substantially match a swirl angle of a fan discharge airflow. 6. A method in accordance with claim 2 further comprising coupling inner wall to an inlet guide vane to utilize the inlet guide vane as a heat sink to reduce the temperature of the lubrication fluid channeled through the splitter. 7. A splitter for a gas turbine engine including a nacelle and a core engine disposed within the nacelle to define a core engine flow path through the core engine and a bypass duct between the core engine and the nacelle, said splitter comprising: a radially inner wall;a radially outer wall connected to said radially inner wall at a leading edge;an inner support structure coupled between said inner and outer walls such that a flowpath is defined between at least a portion of said inner support structure and said inner and outer walls; anda plurality of cooling circuits extending through a portion of the core engine for circulating lubrication fluid therethrough, wherein said plurality of cooling circuits are coupled in flow communication with at least one pumping device, said splitter configured to be coupled to: said core engine to split a flow of air between the core engine flowpath and the bypass duct while reducing a temperature of the lubrication fluid and increasing a temperature of at least a portion of said inner and outer walls; andat least one substantially hollow stator vane of a booster compressor of the gas turbine engine, the at least one substantially hollow stator vane configured to receive lubrication fluid channeled from said splitter via said at least one pumping device. 8. A splitter in accordance with claim 7 wherein said inner support structure further comprises: a central portion; anda plurality of longitudinal structural members coupled between said central portion and said inner wall. 9. A splitter in accordance with claim 8 wherein said cooling circuit comprises a first flowpath portion that is defined between said central portion and said inner wall. 10. A splitter in accordance with claim 7 wherein said inner support structure further comprises: a central portion; anda plurality of radial structural members coupled between said central portion and said outer wall. 11. A splitter in accordance with claim 10 wherein said cooling circuit comprises a second flowpath portion that is defined between said central portion and said outer wall. 12. A splitter in accordance with claim 7 further comprising a plurality of stiffeners coupled to an external surface of said outer wall, each said stiffener having a profile that is configured to substantially match a swirl angle of a fan discharge airflow to enhance heat transfer. 13. A splitter in accordance with claim 7 wherein said inner wall is configured to be coupled to an inlet guide vane such that the inlet guide vane is utilized as a heat sink to reduce the temperature of the lubrication fluid channeled through said splitter. 14. A gas turbine engine comprising: a nacelle;a core engine disposed within said nacelle to define a core engine flow path through said core engine and a bypass duct between said core engine and said nacelle;a booster compressor disposed within said nacelle, said booster compressor comprises at least one substantially hollow stator vane;at least one lubrication fluid pumping device;a splitter coupled to said core engine to split a flow of air between the core engine flow path and the bypass duct, said splitter comprising a first cooling circuit configured to circulate lubrication fluid via said at least one lubrication fluid pumping device such that a temperature of the lubrication fluid is reduced and a temperature of at least a portion of said splitter is increased, said splitter configured to circulate a portion of the lubrication fluid to said at least one substantially hollow stator vane of said booster compressor. 15. A gas turbine engine in accordance with claim 14 wherein said splitter further comprises a radially inner wall, a radially outer wall connected to said radially inner wall at a leading edge, and an inner support structure comprising a central portion and a plurality of longitudinal structural members coupled between said central portion and said inner wall such that a first flowpath portion is defined between said longitudinal structural members, said central portion, and said inner wall. 16. A gas turbine engine in accordance with claim 14 wherein said splitter further comprises a radially inner wall, a radially outer wall connected to said radially inner wall at a leading edge, and an inner support structure comprising a central portion and a plurality of radial structural members coupled between said central portion and said outer wall such that a second flowpath portion is defined between said radial structural members, said central portion, and said outer wall. 17. A gas turbine engine in accordance with claim 14 wherein said splitter further comprises a radially inner wall, a radially outer wall connected to said radially inner wall at a leading edge, and a plurality of stiffeners coupled to an external surface of said outer wall, each said stiffener having a profile that is configured to substantially match a swirl angle of a fan discharge airflow to enhance heat transfer. 18. A gas turbine engine in accordance with claim 14 wherein said splitter further comprises a radially inner wall and a radially outer wall connected to said radially inner wall at a leading edge, said inner wall coupled to an inlet guide vane to utilize said inlet guide vane as a heat sink to reduce the temperature of the lubrication fluid channeled through said splitter. 19. A gas turbine engine in accordance with claim 14 further comprising a booster compressor that comprises at least one substantially hollow stator vane configured to receive lubrication fluid channeled from said splitter.