Patent ID: 8091365

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, 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 having an internal passage extending between an inlet and an outlet; wherein the outlet is offset from the inlet in the longitudinal 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; wherein the first side wall is canted relative to a radial axis when viewing the outlet longitudinally upstream; and wherein the second side wall is canted in a generally same direction as the first side wall relative to a radial axis when viewing the outlet longitudinally upstream; wherein the second side wall is nonparallel to the first side wall of the outlet.