A method for assembling a gas turbine engine (10) that includes providing a low-pressure turbine inner rotor (42) configured to rotate in a first direction, providing a low-pressure turbine outer rotor (38) configured to rotate in a second direction that is opposite the first rotational direction, and coupling at least one foil bearing (100) to at least one of the inner and outer rotors to facilitate improving clearance control between a first rotating component and at least one of a second rotating component and a non-rotating component.