Patent ID: 9650904
Date: 2017-05-16
CPC Classifications: F01D,F05D,F23R

Claim:
1. A transition duct system for delivering hot-temperature gases from a plurality of combustors in a combustion turbine engine to a first row of turbine blades in the combustion turbine engine, the transition duct system comprising: an exit piece for each combustor, wherein each exit piece comprises a straight path segment for receiving a gas flow from a respective combustor, wherein each straight path segment forms a closed perimeter starting at an inlet end of the straight path segment, wherein the closed perimeter of the straight path segment of the exit piece changes to an open perimeter that is in fluid communication with a corresponding portion of an annular chamber along a common plane between a convergence flow junction (CFJ) and an outlet end of the straight path segment, and the exit piece comprising: respective retainer structures disposed in the straight path segment of the exit piece to retain respective edges of the open liner perimeter in the straight path segment of the exit piece, wherein the respective retainer structures are disposed at respective edges of the open perimeter of the straight path segment of the exit piece, wherein each retainer structure comprises a body comprising a first flange and a second flange interconnected by a web, the body having a lengthwise dimension extending along a longitudinal axis of the straight path segment of the exit piece, wherein the first and second flanges interconnected by the web define a groove configured to receive a corresponding ceramic liner protrusion at a respective edge of the open liner perimeter in the straight path segment of the exit piece.