A combustion system includes a fuel distributor configured to output a fuel, an oxidant source configured to output an oxidant, and a mixing tube defining a mixing volume aligned to receive the fuel and oxidant. The mixing tube is shaped to convey the fuel and the oxidant through the mixing volume at a bulk velocity higher than a flame propagation speed. The combustion system includes a flame holder aligned to receive the mixed fuel and oxidant and to support a combustion reaction of the fuel and the oxidant.

A combustion system includes a fuel distributor configured to output a fuel, an oxidant source configured to output an oxidant, and a mixing tube defining a mixing volume aligned to receive the fuel and oxidant. The mixing tube is shaped to convey the fuel and the oxidant through the mixing volume at a bulk velocity higher than a flame propagation speed. The combustion system includes a flame holder aligned to receive the mixed fuel and oxidant and to support a combustion reaction of the fuel and the oxidant.

A nozzle includes a nozzle body defining a longitudinal axis. The nozzle body includes an inner air passage fed by a radial swirler and having a converging conical cross-section. A first fuel circuit is radially outboard from the air passage with respect to the longitudinal axis. A second fuel circuit is radially outboard from the first fuel circuit with respect to the longitudinal axis, wherein each of the first fuel circuit and the second fuel circuit extends from a respective fuel circuit inlet to a respective annular fuel circuit outlet. An outer air passage is defined between a fuel circuit outer wall and an outer air passage wall, wherein the outer air passage is a converging non-swirling outer air passage.

A system and method for igniting liquid fuel in a gas turbine combustor is provided. A liquid fuel cartridge, which is located within the head end, is in flow communication with a liquid fuel supply. A gaseous fuel nozzle is located proximate the liquid fuel cartridge and in flow communication with an auxiliary gaseous fuel supply. A controller is in communication with the liquid fuel supply, the auxiliary gaseous fuel supply, and an igniter located proximate or within the head end. The controller is configured to sequentially: initiate a gaseous fuel flow from the auxiliary gaseous fuel supply to the gaseous fuel nozzle; initiate the igniter to combust the gaseous fuel flow; initiate a liquid fuel flow from the liquid fuel supply to the liquid fuel cartridge; and terminate the gaseous fuel flow from the auxiliary gaseous fuel supply.

The present disclosure is directed to a dual-fuel fuel nozzle including a center body having a tube shape and a gas fuel plenum defined within the center body. The fuel nozzle also includes a plurality of turning vanes extending radially outward from the center body. Each turning vane includes at least one fuel port in fluid communication with the gas fuel plenum. A plurality of apertures is disposed through the plurality of turning vanes. The fuel nozzle further includes a ring manifold disposed within the center body downstream of the plurality of turning vanes. Additionally, the fuel nozzle includes a first fuel tube extending helically around a centerline of the center body. Furthermore, the fuel nozzle includes an air shield disposed within the center body and extending circumferentially around the first fuel tube.

The present disclosure is directed to a nozzle assembly including a header manifold and a ring manifold, which defines a liquid fuel plenum, spaced from the header manifold. An outer sleeve connects to the ring manifold, and a nozzle body connects to the outer sleeve. The ring manifold, the outer sleeve, and the nozzle body define a fluid chamber. An inner fuel tube extends from the header manifold to the nozzle body. A portion of the inner fuel tube extends helically about an axial centerline of the nozzle assembly between the ring manifold and the nozzle body. A first fuel tube extends helically around a portion of the inner fuel tube. The first fuel tube fluidly couples the liquid fuel plenum to the header manifold. A second fuel tube extends helically around a portion of the inner fuel tube and fluidly couples the liquid fuel plenum to the header manifold.

A fuel nozzle body having a rearward end and a front end with an outer tube which extends from the rearward end to the front end and has radial openings for a first fuel in the region of the front end, and an inner tube which is arranged concentrically to the outer tube and which opens in the region of the front end into a nozzle head, which has additional openings for a second fuel, wherein, in the region of the front end, the inner tube is guided in the outer tube by two fits which are arranged axially between the radial openings and the additional openings, and wherein the first fit closest to the radial openings is configured as a circumferential web around the inner tube, and wherein the second fit is configured with at least one interruption on the perimeter.

A nozzle device for feeding a gaseous fuel and a liquid fuel into a combustion chamber of a gas turbine assembly, includes: a nozzle main body having nozzle openings for injecting the gaseous and/or liquid fuels into the combustion chamber, a liquid fuel line for the fluidic connection between a liquid supply line system and the nozzle openings, and at least one gas fuel line for the fluidic connection between a gas supply line system and the nozzle openings. An optimized operation is achieved in that at least partly the gas fuel line is configured to be correlated with the liquid fuel line, wherein a flow cross section AiH2 of the gas fuel line is proportional to a flow cross section AiK of the liquid fuel line by a factor F, where: AiH2=F*Aik, F being 2.4-3, preferably 2.6-2.8, e.g. 2.7.

A combustion system includes a fuel distributor configured to output a fuel, an oxidant source configured to output an oxidant, and a mixing tube defining a mixing volume aligned to receive the fuel and oxidant. The mixing tube is shaped to convey the fuel and the oxidant through the mixing volume at a bulk velocity higher than a flame propagation speed. The combustion system includes a flame holder aligned to receive the mixed fuel and oxidant and to support a combustion reaction of the fuel and the oxidant.

A combustion system includes a fuel distributor configured to output a fuel, an oxidant source configured to output an oxidant, and a mixing tube defining a mixing volume aligned to receive the fuel and oxidant. The mixing tube is shaped to convey the fuel and the oxidant through the mixing volume at a bulk velocity higher than a flame propagation speed. The combustion system includes a flame holder aligned to receive the mixed fuel and oxidant and to support a combustion reaction of the fuel and the oxidant.