Patent ID: 8113003

Claim:
A transition duct for routing gas flow in a combustion turbine subsystem that includes 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, an axis of the rotor assembly 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 having an internal passage extending between an inlet and an outlet; wherein the outlet is offset from the inlet in the longitudinal direction and the tangential direction; wherein the outlet is formed from a radially outer side generally opposite to a radially inner side, and the radially outer and inner sides are coupled together with opposed first and second side walls; and wherein a first side of the transition duct body is configured to be coplanar with a second side of an adjacent transition duct when assembled beside the adjacent transition duct.