Patent ID: 7185484

Claim:
A method of assembling a gas turbine engine, said method comprising: coupling a first turbine shaft that includes m rows of first 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 second 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 a number of rows of turbine blades on each shaft relative to a total number of rows of blades on both shafts, wherein m represents the number of first rows of turbine blades and n represents the number of second rows of turbine blades, and wherein m and n are selected to provide a torque split between the first low pressure turbine shaft and second low pressure turbine shaft of greater than about 1.2:1.