Abstract: The present application provides a fuel nozzle spring support system. The fuel nozzle spring support system may include a fuel nozzle, a cap assembly, and a spring support positioned between the fuel nozzle and the cap assembly.

Abstract: The present application provides a fuel nozzle assembly. The fuel nozzle assembly may include an end cap assembly, a number of fuel nozzles positioned within the end cap assembly, and one or more cup seals. The cup seals may be positioned between the end cap assembly and the fuel nozzles.

Abstract: A combustion liner cap assembly includes a cylindrical outer sleeve. The cylindrical outer sleeve includes a center fuel nozzle opening and a plurality of outer fuel nozzle openings spaced around the center fuel nozzle. A mounting flange assembly concentrically surrounds the cylindrical outer sleeve. A plurality of struts on an outer surface of the cylindrical outer sleeve support the mounting flange assembly. A plurality of flanges are on the outer surface of the cylindrical outer sleeve; and a plurality of support rods having first ends are adjustably supported by respective flanges. A combustor for a gas turbine includes a combustion liner cap assembly, a plurality of outer fuel nozzles supported in the plurality of outer fuel nozzle openings, and a center fuel nozzle supported in the center fuel nozzle opening. Second ends of the plurality of support rods adjustably contact the center fuel nozzle.

Abstract: A combustion liner cap assembly includes a cylindrical outer sleeve. The cylindrical outer sleeve includes a center fuel nozzle opening and a plurality of outer fuel nozzle openings spaced around the center fuel nozzle. A mounting flange assembly concentrically surrounds the cylindrical outer sleeve. A plurality of struts on an outer surface of the cylindrical outer sleeve support the mounting flange assembly. A plurality of flanges are on the outer surface of the cylindrical outer sleeve; and a plurality of support rods having first ends are adjustably supported by respective flanges. A combustor for a gas turbine includes a combustion liner cap assembly, a plurality of outer fuel nozzles supported in the plurality of outer fuel nozzle openings, and a center fuel nozzle supported in the center fuel nozzle opening. Second ends of the plurality of support rods adjustably contact the center fuel nozzle.

Abstract: A combustion liner cap assembly includes a cylindrical sleeve with a cantilevered fuel nozzle mounted therewithin; and a plurality of support rods. Each support rod has a first end supported by the cylindrical sleeve and a second end configured to contact the cantilevered fuel nozzle. Each support rod is adjustable in effective length to provide an adjustable compression force against the cantilevered fuel nozzle. A method for adjusting a resonant frequency of a cantilevered fuel nozzle mounted in a cylindrical sleeve is provided. A plurality of support rods extend between the cylindrical sleeve and the cantilevered fuel nozzle. An associated gas turbine has at least some combustion and rotor tones of interest. The method includes adjusting an effective length of the support rods to adjust compressive forces exerted against the cantilevered fuel nozzle to increase a resonant frequency of the fuel nozzle to be greater than the combustion and rotor tones of interest.

Abstract: Cooling is provided for a gas turbine combustion system that includes a first member, such as a liner, having exterior and interior surfaces that define a wall therebetween and a central area. A second member, such as a cap, is located adjacent that interior surface. A source of cooling gas is in fluid communication with the exterior surface of the first member. An open space, in which is located a hula seal, is located between the interior surface of the first member and the second member. At least one opening in the wall of the first member provides a passageway for the cooling gas from the exterior surface of the first member to the open space. The passageway has a directional axis along which the cooling gas flows and is discharged into the open space. The directional axis is substantially oriented in a direction other than a direction towards the central area of the first member.

Abstract: The present application provides a fuel nozzle assembly. The fuel nozzle assembly may include an end cap assembly, a number of fuel nozzles positioned within the end cap assembly, and one or more cup seals. The cup seals may be positioned between the end cap assembly and the fuel nozzles.

Abstract: The present application provides a fuel nozzle spring support system. The fuel nozzle spring support system may include a fuel nozzle, a cap assembly, and a spring support positioned between the fuel nozzle and the cap assembly.

Abstract: Cooling is provided for a gas turbine combustion system that includes a first member, such as a liner, having exterior and interior surfaces that define a wall therebetween and a central area. A second member, such as a cap, is located adjacent that interior surface. A source of cooling gas is in fluid communication with the exterior surface of the first member. An open space, in which is located a hula seal, is located between the interior surface of the first member and the second member. At least one opening in the wall of the first member provides a passageway for the cooling gas from the exterior surface of the first member to the open space. The passageway has a directional axis along which the cooling gas flows and is discharged into the open space. The directional axis is substantially oriented in a direction other than a direction towards the central area of the first member.