Patent ID: 9151171
Filing Date: 2015-10-06
Classification: F01D

Abstract:
1. A hot gas path system for a gas turbine, comprising: at least one outer housing forming a combustor basket; at least one transition section that extends from a position downstream of a terminal end of the combustor basket; a stepped inlet ring coupled to the at least one transition section and extending upstream from the at least one transition section, wherein an upstream end of the stepped inlet ring is positioned radially outward from the combustor basket such that at least a portion of the stepped inlet ring axially overlaps a portion of the combustor basket, wherein the stepped inlet ring is formed from a radially extending, generally cylindrical collar coupled to an axially extending cylindrical wall; at least one spring clip positioned between the combustor basket and the stepped inlet ring such that the at least one spring clip seals at least a portion of a circumferential gap between the combustor basket and the stepped inlet ring; and at least one heat shield positioned downstream from the combustor basket and proximate to an intersection between the collar and the axially extending cylindrical wall, wherein the at least one heat shield contacts the collar and contacts the axially extending cylindrical wall of the stepped inlet ring.