Abstract: A combustor assembly includes an inner and outer liner defining a combustion chamber. The inner and outer liners include a plurality of cooling holes spaced a specified distance apart. The cooling holes include first, second and third groups. The first group of cooling holes is the most densely spaced, followed by the second group and then the third group. The first group of cooling holes begin upstream of a leading edge of a large opening and terminates downstream of the leading edge. The increased density of cooling holes adjacent the large openings provide increased cooling airflow in areas where cooling may be affected by local disturbances in cooling airflow.

Abstract: A gas turbine engine combustor has inboard and outboard walls. A forward bulkhead extends between the walls and cooperates therewith to define a combustor interior volume. Bluff body fuel injectors are along the bulkhead.

Abstract: An article has a metallic substrate having a first emissivity. A thermal barrier coating atop the substrate may have an emissivity that is a substantial fraction of the first emissivity.

Abstract: An article has a metallic substrate having a first emissivity. A thermal barrier coating atop the substrate may have an emissivity that is a substantial fraction of the first emissivity.

Abstract: A combustor heat shield panel is secured relative to a combustor shell so as to hold the panel exterior surface spaced apart from and facing the shell interior surface over major area of the panel exterior surface. A gap is formed between the heat shield exterior surface and shell interior surface along at least a major portion of the perimeter of the heat shield.

Abstract: A heatshielded article includes a support 18 and at least one heatshield 20 secured adjacent to the support. The heatshield includes a shield portion 28 spaced from the support. The shield portion includes a hot side 30 and an uncoated cold side 32. A projection projects from an origin 36 at the shield portion to a terminus 38 remote from the shield portion. The terminus includes a protective coating 64 along at least a portion of its length.

Abstract: A gas turbine engine combustor has inboard and outboard walls. A forward bulkhead extends between the walls and cooperates therewith to define a combustor interior volume. In longitudinal section, a first portion of the combustor interior volume converges from fore to aft and a second portion, aft of the first portion converges from fore to aft more gradually than the first portion.

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.

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 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.