Patent ID: 8015818
Filing Date: 2011-09-13
Classification: F01D,F05D

Abstract:
1. A transition duct for a gas turbine engine for conducting hot combustion gas along a direction of flow between a combustor outlet and a turbine inlet, the transition duct comprising: a plurality of panels, each panel formed to define a corner region extending longitudinally in a direction generally parallel to the direction of flow; a plurality of subsurface cooling channels formed through the corner region of each panel, the cooling channels being part of a closed cooling scheme and extending longitudinally in a direction parallel to the direction of flow and effective to cool the entire respective corner region; and a weld joining edges of adjacent panels remote from the corner region; an upper panel and a lower panel each formed with two corner regions to define respective U-shapes; welds joining the upper panel and lower panel along respective opposed edges remote from the corner regions; and further comprising each corner region comprising a minimum radius of curvature of at least 35 mm.