This paper is concerned with thermal analysis and life prediction in the after shell section of a gas turbine combustion liner with internal cooling passages known as a C-channel. Heat transfer, temperature, and stress distributions are calculated via 3D-numerical simulations, which are carried out using FVM and FEM commercial software packages. From startup to shutdown, high thermal deformation occurs between the hot and coolant side walls in the welding region, the nearby cooling hole, and above the divider of the C-channel. Three regions are therefore very weak in relation to the thermal cycle. Moreover, these locations are in close agreement with the locations of thermal cracks in an actual gas turbine combustor currently in service.
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