Abstract: A combustor for a gas turbine including a casing, a flow sleeve at least partially disposed within the casing, a combustion liner at least partially disposed within the flow sleeve, a liner stop feature extending from the combustion liner, and a liner guide stop including a first end separated from a second end, the second end configured to be at least partially engaged with the liner stop feature, wherein the liner guide stop extends through the casing and the flow sleeve.

Abstract: A method is provided for operating an air-staged diffusion nozzle for a gas turbine combustor to cool the nozzle tip and improve mixing of gas fuel and air within a downstream burner space. Air is mixed with the gas-fuel in an outer swirler and expanded in a downstream burner tube space. Compressed air from a cooling air cavity in the nozzle flows through an inner swirler, passing downstream from the tip of the nozzle to the burner tube space, cooling the nozzle tip and improving the mixing of the gas-fuel with air, thereby reducing emissions from the gas turbine and reducing soot formation in startup. Direction and rotation of the discharged air from the nozzle tip into the burner space may be arranged to promote nozzle tip cooling and gas-fuel mixing with air.

Abstract: In an air-staged diffusion nozzle for a gas turbine combustor, air is mixed with the gas fuel and expanded in a downstream burner tube. Introduction of air, passing downstream from the tip of the nozzle to the burner tube space forces hot gases away from and cools the nozzle tip. Air flow through an inner swirler or through cooling holes on the nozzle tip may be arranged to establish a cooling flow volume and direction that advantageously interacts with gas fuel-air flow from an outer swirler to improve fuel-air mixing in the burner tube, helping to reduce emissions and soot formation.

Abstract: A combustor for a gas turbine including a casing, a flow sleeve at least partially disposed within the casing, a combustion liner at least partially disposed within the flow sleeve, a liner stop feature extending from the combustion liner, and a liner guide stop including a first end separated from a second end, the second end configured to be at least partially engaged with the liner stop feature, wherein the liner guide stop extends through the casing and the flow sleeve.

Abstract: A fuel nozzle for a turbine combustor includes a nozzle head configured to supply a fuel/air mixture to a burner tube attached to said nozzle head and extending downstream of the nozzle head. The burner tube is provided with plural holes for introducing a fluid into the burner tube to thereby treat (e.g., cool) an interior wall of the burner tube by effusion.

Abstract: A system including a controller. The controller may receive a signal indicative of an emissions level of a turbine. The controller may also generate at least one control signal. This control signal may control a split of diluent between a first and a second mixing chamber, whereby the first and the second mixing chambers are located in a fuel nozzle in the turbine.

Abstract: A method is provided for operating an air-staged diffusion nozzle for a gas turbine combustor to cool the nozzle tip and improve mixing of gas fuel and air within a downstream burner space. Air is mixed with the gas-fuel in an outer swirler and expanded in a downstream burner tube space. Compressed air from a cooling air cavity in the nozzle flows through an inner swirler, passing downstream from the tip of the nozzle to the burner tube space, cooling the nozzle tip and improving the mixing of the gas-fuel with air, thereby reducing emissions from the gas turbine and reducing soot formation in startup. Direction and rotation of the discharged air from the nozzle tip into the burner space may be arranged to promote nozzle tip cooling and gas-fuel mixing with air.

Abstract: In an air-staged diffusion nozzle for a gas turbine combustor, air is mixed with the gas fuel and expanded in a downstream burner tube. Introduction of air, passing downstream from the tip of the nozzle to the burner tube space forces hot gases away from and cools the nozzle tip. Air flow through an inner swirler or through cooling holes on the nozzle tip may be arranged to establish a cooling flow volume and direction that advantageously interacts with gas fuel-air flow from an outer swirler to improve fuel-air mixing in the burner tube, helping to reduce emissions and soot formation.

Abstract: A combustor for a gas turbine engine that includes first and second combustion chambers interconnected by a throat region that includes a converging wall section, a diverging wall section, and a throat apex between the diverging wall section and the converging wall section; a plurality of cooling apertures disposed on the converging wall section; and a cooling slot disposed on the diverging wall section; wherein: the cooling apertures comprise apertures through the thickness of the converging wall section; and the cooling slot comprising a circumferentially extending slot through the length of the diverging wall section.

Abstract: A nozzle includes first, second, and third ports each angled to direct a first, second, and third fluid in a first, second, and third rotational direction, respectively. The first, second, and third fluids are selected from the group consisting of a first fuel, a second fuel, a diluent, and a compressed working fluid. A method for supplying fuel through a nozzle includes injecting a first fluid through first ports in a first rotational direction, injecting a second fluid through second ports in a second rotational direction, and injecting a third fluid through third ports in a third rotational direction. The method further includes selecting the first, second, and third fluids from the group consisting of a first fuel, a second fuel, a diluent, and a compressed working fluid.

Abstract: A method includes receiving fuel and air into a cup of a turbine fuel nozzle. The method also includes mixing the fuel and air at least partially within the cup. In addition, the method includes directing a fuel air mixture toward a turbine combustor. The method also includes shielding an inner wall of the cup with a blanket of a protective fluid flow to reduce the possibility of flame holding along the inner wall. The protective fluid flow excludes a combustible mixture of fuel and air.