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 fuel nozzle including a center body having a tube shape and a ring manifold disposed at an aft end of the center body. The fuel nozzle also includes an inner tube extending axially through the ring manifold and disposed within the center body. The inner tube is in fluid communication with a diluent supply. The fuel nozzle further includes a fuel tube extending helically around a portion of the inner tube. The fuel tube fluidly couples a fuel plenum of the ring manifold to a liquid fuel supply. Furthermore, the fuel nozzle includes a plurality of fuel injectors circumferentially spaced within an outer band of the ring manifold and in fluid communication with the fuel plenum. Each fuel injector is oriented to direct atomized liquid fuel radially outward from the center body. The ring manifold and the inner tube are thermally decoupled.

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 gas burner includes: a nozzle where gas fuel flows; and a primary air supply part for supplying, from around the nozzle, primary air whose air ratio to the gas fuel is less than 1. The nozzle includes: at least one main hole configured to eject the gas fuel at an ejection angle of not less than 25 degrees and not greater than 45 degrees with respect to a central axis of the gas burner; and at least one sub hole configured to eject the gas fuel at an ejection angle of not less than 35 degrees and not greater than 55 degrees with respect to the central axis of the gas burner, the ejection angle of the sub hole being greater than the ejection angle of the main hole. The gas fuel flowing in the nozzle has a gas pressure of not less than 300 kPa.

A method and a boiler for burning a liquid or gaseous fuel. The boiler comprises a boiler housing with a cylindrical heat exchanger arranged therein and has slot-like pass-through openings for the combustion gases and has a flame tube. A flame-deflecting part for deflecting the combustion gases at a right angle is provided at an axial distance from the flame tube. The flame tube contains a baffle plate with a faceplate through which combustion air is fed into the flame tube. A blower ensures the supply of combustion air into the combustion chamber. Blower pressure is so that a differential pressure zone with a differential pressure of at least 0.25 mbar is generated between the flame tube and the heat exchanger, downstream of the faceplate at full load of the burner in relation to the pressure in the combustion chamber in the region of the recirculation slots.

A nozzle device for feeding fuel into a combustion chamber of a gas turbine assembly, includes: a nozzle main body having nozzle openings for injecting the fuel into the combustion chamber; a nozzle bracket having a fuel line for fluidic connection between a manifold fuel line and the main body, wherein at least a portion of the fuel line is aligned along, a central longitudinal axis; and a throttle element disposed downstream of the manifold fuel line for throttling the fuel flow to a pre-specified target quantity. The throttle element includes two stages which are fluidically disposed in series, each stage having a line portion aligned along a central longitudinal axis and a flow cross section. A relaxation chamber is disposed between the stages, the flow cross section of the relaxation chamber being larger than the flow cross section of the upstream stage.

A nozzle for a combustor is disclosed. The nozzle may include a main fuel passage (202), a number of radial fuel ports (206) in communication with the main fuel passage, a prefilmer surface (212) in communication with the radial fuel ports, and a main purge air passage (218) in communication with the radial fuel ports and the prefilmer surface.

A fire safety protection evaluation system includes at least one horizontal collection device and at least one vertical collection device. The at least one horizontal collection device includes a liquid collection pan with a substantially horizontal opening, a first storage container in communication with the liquid collection pan, and a first measuring device to measure an amount of liquid in the first storage container and/or a rate of liquid entering the first storage container. The at least one vertical collection device includes a substantially vertical liquid collection surface extending between a top edge and a bottom edge, a trough located along the bottom edge to collect liquid from the substantially vertical collection surface, and a second measuring device to measure an amount of liquid and/or a rate of liquid collected by the trough.

A multi-functional fuel nozzle (10) for a combustion turbine engine is provided. An annular fuel-injecting lance (12) may include a first fluid circuit (14) and a second fluid circuit (16). One of the first and second fluid circuits during a liquid fuel operating mode of the combustion turbine engine may convey a liquid fuel. The other of the first and second fluid circuits may convey a selectable non-fuel fluid. An atomizer (30) is disposed at the downstream end of the lance. The atomizer may have a first ejection orifice (32) responsive to the first fluid circuit to form a first atomized ejection cone (34), and a second ejection orifice (36) responsive to the second fluid circuit to form a second atomized ejection cone (38). The first and second ejection cones (34, 38) formed with the atomizer may be concentric cones that intersect with one another over a predefined angular range.