one known differential bearing that is coupled between the concentric low pressure shafts when an even number of total stages are used in at least one known counter rotating low pressure turbine moreover utilizing straddle mounted low pressure turbine 200 facilitates reducing the weight of gas turbine engine 10 by eliminating a large over turning moment generated by a known low pressure turbine that includes an outer rotor having an even number of stages the exemplary embodiments described above illustrate a counter rotating low pressure turbine having an outer rotor that includes an even number of stages and an inner rotor that includes an odd number of stages such that the outer rotor straddles the inner rotor since the outer rotor straddles the inner rotor the outer rotor is configurable to couple to either the forward or aft fan assembly utilizing a straddle mounted counter rotating low pressure turbine facilitates reducing the weight of the gas turbine engine by eliminating the large over turning moment of a conventional low pressure turbine that includes an outer rotor having an even number of stages moreover the straddle mounted turbines described herein facilitate handling a blade out event in which a large turbine unbalance may result in the outer rotating casing while also improving gas turbine engine performance by providing increased tip clearance control between the outer rotor and the casing moreover the straddle mounted turbines described herein facilitate reducing the weight of the turbine rear frame by distributing the weight of the outer rotor between the turbine mid frame and turbine rear frame exemplary embodiments of straddle mounted counter rotating low pressure turbines are described above.