A gas turbine engine comprising: a compressor section having at least a first compressor portion and a second compressor portion; a combustor fluidly connected to the compressor section; a turbine section fluidly connected to the combustor section, the turbine section having at least a first turbine portion and a second turbine portion; a first shaft connecting the first compressor section and the first turbine section; a second shaft connecting the second compressor section and the second turbine section, wherein the second shaft is at least partially disposed within the first shaft, and wherein the second shaft includes a radially protruding threading portion; and a variable positioner (140; 240) disposed about said second shaft, the variable positioner (140; 240) being a cylindrical component defining a radially outward facing surface (147; 292) and a first and second axial end surface (148; 248, 290), wherein the variable positioner (140; 240) includes a radially inward facing threading section (142; 242), and wherein said radially inward facing threading section (142; 242) of said variable positioner (100; 240) interfaces with said radially protruding threading portion of said second shaft, wherein said variable positioner further comprises at least one anti-rotation slot (146; 293) positioned on said radially outward facing surface (147; 292), the anti-rotation slot interfacing with an interface surface of a rotating component; wherein said at least one anti-rotation slot (146; 293) interfaces with an anti-rotation feature of said rotor, thereby preventing rotation of the variable positioner relative to the second shaft, a rotor having an interface surface contacting a surface (148; 248) of said variable positioner (140; 240). a compressor section having at least a first compressor portion and a second compressor portion; a combustor fluidly connected to the compressor section; a turbine section fluidly connected to the combustor section, the turbine section having at least a first turbine portion and a second turbine portion; a first shaft connecting the first compressor section and the first turbine section; a second shaft connecting the second compressor section and the second turbine section, wherein the second shaft is at least partially disposed within the first shaft, and wherein the second shaft includes a radially protruding threading portion; and a variable positioner (140; 240) disposed about said second shaft, the variable positioner (140; 240) being a cylindrical component defining a radially outward facing surface (147; 292) and a first and second axial end surface (148; 248, 290), wherein the variable positioner (140; 240) includes a radially inward facing threading section (142; 242), and wherein said radially inward facing threading section (142; 242) of said variable positioner (100; 240) interfaces with said radially protruding threading portion of said second shaft, wherein said variable positioner further comprises at least one anti-rotation slot (146; 293) positioned on said radially outward facing surface (147; 292), the anti-rotation slot interfacing with an interface surface of a rotating component; wherein said at least one anti-rotation slot (146; 293) interfaces with an anti-rotation feature of said rotor, thereby preventing rotation of the variable positioner relative to the second shaft, a rotor having an interface surface contacting a surface (148; 248) of said variable positioner (140; 240).