A gas turbine engine comprising: a core engine; a fan assembly a booster compressor downstream from said fan assembly; at least one pumping device; and a splitter circumscribing said booster, said splitter comprising: a radially inner wall, a radially outer wall connected to said radially inner wall at a leading edge and an inner support structure coupled between said inner and outer walls such that a flowpath is defined between at least a portion of the inner support structure and said inner and outer walls; and a plurality of cooling circuits extending through a portion of the splitter for circulating lubrication fluid therethrough, wherein said plurality of cooling circuits comprise a first flowpath portion that is defined between a central portion of said inner support structure and said inner wall, and are coupled in flow communication with said at least one pumping device, the splitter being configured to be coupled to said core engine to split a flow of air between the core engine flowpath and a bypass duct of the gas turbine engine while reducing a temperature of the lubrication fluid and increasing a temperature of at least a portion of the inner and outer walls; and at least one substantially hollow second stator stage of the booster compressor of the gas turbine engine, the at least one substantially hollow second stator stage configured to receive lubrication fluid channeled from said splitter via said at least one pumping device; the splitter 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. a core engine; a fan assembly a booster compressor downstream from said fan assembly; at least one pumping device; and a splitter circumscribing said booster, said splitter comprising: a radially inner wall, a radially outer wall connected to said radially inner wall at a leading edge and an inner support structure coupled between said inner and outer walls such that a flowpath is defined between at least a portion of the inner support structure and said inner and outer walls; and a plurality of cooling circuits extending through a portion of the splitter for circulating lubrication fluid therethrough, wherein said plurality of cooling circuits comprise a first flowpath portion that is defined between a central portion of said inner support structure and said inner wall, and are coupled in flow communication with said at least one pumping device, the splitter being configured to be coupled to said core engine to split a flow of air between the core engine flowpath and a bypass duct of the gas turbine engine while reducing a temperature of the lubrication fluid and increasing a temperature of at least a portion of the inner and outer walls; and at least one substantially hollow second stator stage of the booster compressor of the gas turbine engine, the at least one substantially hollow second stator stage configured to receive lubrication fluid channeled from said splitter via said at least one pumping device; the splitter 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. a radially inner wall, a radially outer wall connected to said radially inner wall at a leading edge and an inner support structure coupled between said inner and outer walls such that a flowpath is defined between at least a portion of the inner support structure and said inner and outer walls; and a plurality of cooling circuits extending through a portion of the splitter for circulating lubrication fluid therethrough, wherein said plurality of cooling circuits comprise a first flowpath portion that is defined between a central portion of said inner support structure and said inner wall, and are coupled in flow communication with said at least one pumping device, the splitter being configured to be coupled to said core engine to split a flow of air between the core engine flowpath and a bypass duct of the gas turbine engine while reducing a temperature of the lubrication fluid and increasing a temperature of at least a portion of the inner and outer walls; and at least one substantially hollow second stator stage of the booster compressor of the gas turbine engine, the at least one substantially hollow second stator stage configured to receive lubrication fluid channeled from said splitter via said at least one pumping device; the splitter 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.