Abstract: Methods and apparatus for assembling a gas turbine engine are provided. The method includes coupling a first turbine shaft that includes m rows of turbine blades within the gas turbine such that the first turbine shaft is rotatable in a first direction, and coupling a second turbine shaft that includes n rows of turbine blades within the gas turbine such that the second turbine shaft is rotatable in a second direction wherein a torque split between the first and second turbine shafts is substantially proportional to the number of rows of turbine blades on each shaft relative to a total number of rows of blades on both shafts, and wherein m and n are selected to provide a torque split between the first turbine shaft and second turbine shaft of greater than about 1.2:1.