Abstract: A combustor (10) includes a cap (16), a liner (20), a transition piece (24), and a combustion chamber (22) located downstream from the cap (16) and defined by the cap and liner. A secondary nozzle (40) circumferentially arranged around the liner (20) or transition piece (24) includes a center body, a fluid passage through the center body, a shroud circumferentially surrounding the center body, and an annular passage between the center body and the shroud. A method for supplying fuel to a combustor (10) includes flowing fuel through a primary nozzle radially disposed in a breech end of the combustor and flowing fuel through a secondary nozzle (40) circumferentially arranged around and passing through at least one of a liner (20) or a transition piece. The secondary nozzle (40) includes a center body, a fluid passage through the center body, a shroud circumferentially surrounding at least a portion of the center body (44), and an annular passage between the center body and the shroud.

Abstract: A transition duct for a combustor of a gas turbine generally includes a transition duct having a frame at an aft end of the transition duct. The frame generally includes a downstream end, a radially outer portion, a radially inner portion opposed to the radially outer portion, a first side portion between the radially outer and inner portions, and a second side portion opposed to the first side portion. A slot in the first side portion of the frame may have a downstream surface adjacent to the downstream end of the frame. A heat shield having an inner surface, an outer surface and a plurality of spacers may extend generally outward from the heat shield inner surface such that the inner surface is adjacent to the slot downstream surface and the frame downstream end.

Abstract: A combustor (10) includes a cap (16), a liner (20), a transition piece (24), and a combustion chamber (22) located downstream from the cap (16) and defined by the cap and liner. A secondary nozzle (40) circumferentially arranged around the liner (20) or transition piece (24) includes a center body, a fluid passage through the center body, a shroud circumferentially surrounding the center body, and an annular passage between the center body and the shroud. A method for supplying fuel to a combustor (10) includes flowing fuel through a primary nozzle radially disposed in a breech end of the combustor and flowing fuel through a secondary nozzle (40) circumferentially arranged around and passing through at least one of a liner (20) or a transition piece. The secondary nozzle (40) includes a center body, a fluid passage through the center body, a shroud circumferentially surrounding at least a portion of the center body (44), and an annular passage between the center body and the shroud.

Abstract: A transition duct for a combustor of a gas turbine generally includes a transition duct having a frame at an aft end of the transition duct. The frame generally includes a downstream end, a radially outer portion, a radially inner portion opposed to the radially outer portion, a first side portion between the radially outer and inner portions, and a second side portion opposed to the first side portion. A slot in the first side portion of the frame may have a downstream surface adjacent to the downstream end of the frame. A heat shield having an inner surface, an outer surface and a plurality of spacers may extend generally outward from the heat shield inner surface such that the inner surface is adjacent to the slot downstream surface and the frame downstream end.

Abstract: A transition piece aft-frame seal assembly may include an elongate body including a first side and a second side. The seal assembly may also include at least one feed hole disposed on the first side of the body. The seal assembly may also include at least one passageway extending through the body from the first side to the second side and in communication with the at least one feed hole. Moreover, the seal assembly may include at least one cooling hole disposed at the second side of the body and in communication with the at least one passageway. A flow of cooling fluid may enter the at least one feed hole, the at least one passageway, and the at least one cooling hole, wherein the at least one cooling hole directs the flow of cooling fluid to a recirculation zone about adjacent transition piece aft-frame assemblies.

Abstract: A sleeve component assembly for a combustor, and a method for forming the sleeve component assembly for the combustor, are disclosed. The sleeve component assembly includes a sleeve component, the sleeve component comprising one of an inner sleeve component or an outer sleeve component. The sleeve component assembly further includes at least one support feature extending from the sleeve component, the at least one support feature configured to contact and provide vibratory support to an adjacent sleeve component. The at least one support feature is integral with the sleeve component.