Patent ID: 8065881
Filing Date: 2011-11-29
Classification: F01D,Y02T

Abstract:
1. 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; a throat having a cross-sectional area that is less than other aspects of the transition duct body; wherein the outlet is offset from the inlet in the longitudinal direction; wherein an axis of the transition duct body is generally linear; and wherein the outlet is configured such that a first side of the outlet of a first transition duct is coplanar with a second side of a second transition duct assembled beside the second transition duct; the transition duct further comprising a first exhaust mouth positioned in a sidewall and extending from a downstream end of the transition duct body toward the throat, wherein a bottom edge of the first exhaust mouth is substantially coplanar with an inner surface of a first sidewall forming the transition duct body.