Abstract: A fuel nozzle for a gas turbine includes a nozzle body having a tip portion, the nozzle body including an inner tube defining an axially extending air passage; an intermediate tube concentrically arranged and radially spaced from the inner tube and defining a diffusion fuel passage therebetween; and an outer tube concentrically arranged and radially spaced from the intermediate tube and defining a premix fuel passage therebetween. The outer tube has a plurality of radially extending injectors in communication with the premix fuel passage. The premix fuel passage is further defined in part by an outer tube wall portion formed with at least one weakened region adapted to burn through in the event of a flashback, thereby causing a substantial portion of premix fuel to bypass the injectors and to exit the nozzle body at the at least one weakened region. A related method is also disclosed.

Abstract: A method of operating a combustor for a turbine includes flowing fuel through a symmetrical annular array of fuel nozzles to provide an asymmetrical fuel pattern across the combustor. The asymmetrical fuel flow is provided during a diffusion mode of operation prior to transition between the diffusion mode and a premixed mode of operation, during the transition and during the premixed mode of operation. Near full power, the fuel is supplied equally among the fuel nozzles operating in the premixed mode. The asymmetric fuel flow stabilizes the combustor and inhibits high amplitude combustion noise while achieving low emission operation in the premixed mode.

Abstract: The liner cap assembly includes an outer tubular sleeve, an inner cowl and a cone portion extending between the outer sleeve and the inner cowl. The cone portion includes a plurality of annular, concentrically arranged directional vanes on a downstream surface of the cone portion. At least the inner cowl and the cone portion are formed by casting. Plural apertures are formed in the cone portion during casting or after casting.

Abstract: A single nozzle combustion liner cap assembly is provided in the form of an outer annular sleeve connected to an inner center ring or cowl by an angled web or cone portion formed with multiple arrays of holes for introducing air through the cone portion where it is then diverted in desired directions by cooling slots formed by integral baffles or vanes formed on the downstream side of the cone portion. In one exemplary embodiment, three baffles or directional vanes are provided on the cone portion, the two innermost of which direct air radially inwardly along the downstream surface of the cone toward the cowl, and the third of which directs air in two opposite directions, i.e., inwardly and outwardly along the cone portion.

Abstract: A modular combustion liner cap assembly (42) for use in a multi-nozzle combustor of a gas turbine includes a substantially cylindrical first sleeve (46) having a rearward end and a forward end; a rear plate (48) fixed to the rearward end of the sleeve (46), the rear plate (48) provided with a first plurality of openings (52) for receiving a corresponding number of fuel nozzles (32); a forward plate subassembly (68) fixed to the forward end of the sleeve (46), the forward plate provided with a second plurality of openings (80) in substantial alignment with the first plurality of openings in the rear plate (48); a plurality of open ended premix tubes having forward and rearward ends, each tube (96) extending axially within the sleeve (46) between the rear plate (48) and the forward plate assembly (68), each premix tube (96) supported within a corresponding one of the first plurality of openings (52) at its rearward end and a corresponding one of the second plurality of openings (80) at its forward end.

Abstract: A spring biased bearing is slidably mounted within a clevis joint so as to apply a frictional damping force to a flap of a jet engine exhaust nozzle. A forward hinge joint restrains the bearing against rotation with the flap while an aft hinge joint provides for both rotation and translation of the bearing about the flap. A tubular canister may be used with the hinge joint to preset the axial compression and biasing force generated by a coil spring enclosed within the canister.