Abstract: A method for assembling a combustor assembly is provided. The method includes providing at least one sleeve having a plurality of inlets, and coupling at least one airfoil to at least one of the plurality of inlets defined in the at least one sleeve. The airfoil includes a pair of opposing sidewalls coupled together at a leading edge and at a trailing edge and at least one channel is formed between the airfoil sidewalls for channeling cooling air. The cooling air is directed to flow substantially perpendicularly to a direction of air flowing around the airfoil in a portion of the combustor assembly that is to be cooled. The method also includes coupling the at least one sleeve around the portion of the combustor assembly to be cooled. Also provided are a sleeve and an airfoil for use in a combustor assembly.

Abstract: A method for cooling a combustor assembly having a cooling passage. The method includes providing at least one thimble including an inner surface that defines a first opening, a second opening that is downstream from the first opening, and a flow channel that extends between the first opening and the second opening. The flow channel has a converging portion and a recovery portion that is downstream from the converging portion. The method also includes inserting the at least one thimble into at least one inlet that is defined in at least one sleeve such that cooling air is discharged from the flow channel into the cooling passage.

Abstract: A method for cooling a combustor assembly having a cooling passage. The method includes providing at least one thimble including an inner surface that defines a first opening, a second opening that is downstream from the first opening, and a flow channel that extends between the first opening and the second opening. The flow channel has a converging portion and a recovery portion that is downstream from the converging portion. The method also includes inserting the at least one thimble into at least one inlet that is defined in at least one sleeve such that cooling air is discharged from the flow channel into the cooling passage.

Abstract: An aft frame adapted to interface between a combustor transition piece and a first stage turbine nozzle includes: a closed-periphery frame comprised of a top, bottom and pair of side walls. A plurality of cooling holes or apertures having elliptical or oval cross-sectional shapes are provided in one or more of the top, bottom and pair of side walls, extending axially through the closed-periphery frame. The cooling holes have major and minor axes arranged such that the major axes are substantially parallel with the top and bottom walls.

Abstract: A method for assembling a combustor assembly is provided. The method includes providing at least one sleeve having a plurality of inlets, and coupling at least one airfoil to at least one of the plurality of inlets defined in the at least one sleeve. The airfoil includes a pair of opposing sidewalls coupled together at a leading edge and at a trailing edge and at least one channel is formed between the airfoil sidewalls for channeling cooling air. The cooling air is directed to flow substantially perpendicularly to a direction of air flowing around the airfoil in a portion of the combustor assembly that is to be cooled. The method also includes coupling the at least one sleeve around the portion of the combustor assembly to be cooled. Also provided are a sleeve and an airfoil for use in a combustor assembly.