Patent ID: 9416969
Filing Date: 2016-08-16
CPC Classification: F01D,F23R

Claim Text:
1. A combustion system for a gas turbine engine, comprising: a combustor assembly comprising a combustor basket having a liner and a downstream terminal end; a transition duct extending downstream from the combustor basket and having an upstream end located adjacent to the downstream terminal end of the combustor basket; an inlet ring adapter affixed to the upstream end of the transition duct, the inlet ring adapter extending downstream of the upstream end of the transition duct in overlapping relation to an inner surface of the transition duct; a spring clip assembly mounted to the downstream terminal end of the combustor basket and resiliently biased into engagement with an inwardly facing surface of the inlet ring adapter forming a coupling between the combustor basket and the transition duct; and wherein the transition duct is a single piece that has a radial step wall at the upstream end to define a first larger diameter adjacent to a cylindrical sleeve of the inlet ring adapter and a second smaller diameter extending in a direction distal from the inlet ring adapter, wherein the radial step wall extends perpendicularly from the inner surface of the transition duct to a second inner surface of the transition duct; and wherein the cylindrical sleeve of the inlet ring adapter extends generally parallel to the transition duct between the liner and the inlet ring adapter, and comprises a flange portion extending perpendicular to the cylindrical sleeve and attached to the upstream end of the transition duct.