Patent ID: 9133721
Filing Date: 2015-09-15
Classification: F01D,F05D

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: wherein the duct body is formed at least in part from a multi-panel outer wall; and wherein the multi-panel outer wall is formed from a lower section formed from an inner panel having an inner surface that defines at least a portion of the hot gas path plenum, an intermediate panel positioned radially outward from the inner panel such that at least one cooling chamber is formed between the inner and intermediate panels and an outer panel positioned radially outward from the intermediate panel; an attachment system comprising at least one seal body integrally formed with the inner panel of the lower section and having at least one portion extending radially outward with at least one pocket configured to receive a side edge of the intermediate panel of the lower section in a sliding arrangement such that the intermediate panel is able to move in-plane relative to the attachment system and to receive a side edge of the outer panel in a sliding arrangement such that the outer panel is able to move in-plane relative to the attachment system.