Abstract: A method for casting a workpiece comprising the steps of applying a protective coating to a base core the base core comprising, a metal strip comprising a generally planar expanse, a plurality of tabs arranged in a pattern upon the metal strip each of the tabs comprising a base end, a terminus end, and a tab shaft extending from the base end to the terminus end wherein each of the tabs is angularly displaceable about each the base end of the tabs, injecting a molding substance about the tabs of the base core, encapsulating the base core in a shell, removing the molding substance, casting the base core, and removing the base core.

Abstract: A combustor for a gas turbine engine is provided which includes a plurality of liner segments and a support shell. The support shell includes an interior and an exterior surface, a plurality of mounting holes, and a plurality of impingement coolant holes extending through the support shell. Each liner segment includes a panel and a plurality of mounting studs. The panel includes a face surface and a back surface, and a plurality of normal or inclined coolant holes extending therethrough. The back surface of the panel has a surface profile for improving the heat transfer properties of a liner segment without substantial increase in pressure drop across the combustor.