A combustion turbine subsystem comprising: a transition duct for routing a gas flow in the combustion turbine subsystem; a first stage blade array having a plurality of blades extending in a radial direction from a rotor assembly for rotation in a circumferential direction, said circumferential direction having a tangential direction component, the rotor assembly axis defining a longitudinal direction; and at least one combustor located longitudinally upstream of the first stage blade array and located radially outboard of the first stage blade array, said transition duct comprising: a transition duct body including an internal passage extending between an inlet and an outlet, wherein the transition duct body is located between the combustor and the first stage blade array to receive gas flow from the combustor into the internal passage through the inlet and to discharge the gas flow via the outlet toward the first stage blade array; an exhaust gas diverter section positioned between a substantially linear inlet section extending downstream from the inlet of the transition duct body and a substantially linear outlet section extending downstream to the outlet of the transition duct body, wherein a longitudinal axis of the inlet section is generally parallel to the longitudinal direction defined by the rotor assembly axis, wherein the exhaust gas diverter section is curved such that a longitudinal axis of the outlet section is nonparallel with the longitudinal direction defined by the rotor assembly axis; wherein the outlet is offset from the inlet in the longitudinal direction, the radial direction and the tangential direction; and wherein the curving of the exhaust gas diverter section is such that the outlet section of the transition duct body discharges gas flow in a direction that is at an angle between the longitudinal direction and the tangential direction for direct presentation to the first stage blade array. a transition duct body including an internal passage extending between an inlet and an outlet, wherein the transition duct body is located between the combustor and the first stage blade array to receive gas flow from the combustor into the internal passage through the inlet and to discharge the gas flow via the outlet toward the first stage blade array; an exhaust gas diverter section positioned between a substantially linear inlet section extending downstream from the inlet of the transition duct body and a substantially linear outlet section extending downstream to the outlet of the transition duct body, wherein a longitudinal axis of the inlet section is generally parallel to the longitudinal direction defined by the rotor assembly axis, wherein the exhaust gas diverter section is curved such that a longitudinal axis of the outlet section is nonparallel with the longitudinal direction defined by the rotor assembly axis; wherein the outlet is offset from the inlet in the longitudinal direction, the radial direction and the tangential direction; and wherein the curving of the exhaust gas diverter section is such that the outlet section of the transition duct body discharges gas flow in a direction that is at an angle between the longitudinal direction and the tangential direction for direct presentation to the first stage blade array.