A cartridge tip includes a main body having an outer annular wall and an inner core each extending between a respective upstream end and a respective downstream end. The inner core is radially spaced apart from the outer annular wall such that an annular air passage is defined at least partially between the outer annular wall and the inner core. A pilot fuel circuit extends between a pilot inlet defined in the upstream end of the inner core and a pilot outlet defined in a downstream end of the inner core. The pilot fuel circuit extends at least partially along an axial centerline of the cartridge tip. A main fuel circuit extends between a main inlet in the upstream end of the inner core and a plurality of main outlets circumferentially spaced apart from one another and disposed upstream from the from the pilot outlet.

Disclosed is a dual-fuel heater having one or more thermocouples that operate a control valve that, in turn, controls whether fuel is distributed from a regulator to a burner based on the signal generated by the thermocouple(s). Further disclosed is a primary fuel selector valve that selects the fuel being used based on the operation of a user. The primary fuel selector valve provides fuel to the control valve upstream from the thermocouples, allowing for upstream control mechanisms such as a slave valve, to control the flow of fuel to the control valve.

Disclosed is a dual-fuel heater having one or more thermocouples that operate a control valve that, in turn, controls whether fuel is distributed from a regulator to a burner based on the signal generated by the thermocouple(s). Further disclosed is a primary fuel selector valve that selects the fuel being used based on the operation of a user. The primary fuel selector valve provides fuel to the control valve upstream from the thermocouples, allowing for upstream control mechanisms such as a slave valve, to control the flow of fuel to the control valve.

A variable-direction burner tip is coupled to a first actuator that, when actuated, alters a firing direction of the respective burner tip. A respective flexible hose may couple a fuel input to each burner tip to accommodate rotation of the respective burner tip. In a burner incorporating one or more variable-direction burner tips, the burner includes a burner throat having one or more burner throats therein, the burner throats being sized and shaped to accommodate variation in firing direction by at least one burner tip positioned within each of the burner throats.

A burner and methods of using the burner. The burner produces a flame from combustion air and fuel gas. Flue gas, also produced, can be withdrawn and recycled to the burner. A cooling or condition gas, such as ambient air, may be mixed with the flue gas to reduce its temperature. The burner may also utilize a stage injection so that a portion of the produced flue gas is recycled internally.

A fuel supply system for an aircraft engine, comprises a gaseous fuel source and a fuel nozzle. The fuel nozzle includes a housing having a housing interior chamber and a fuel swirler disposed inside the housing interior chamber. The fuel swirler is fluidly connected to the gaseous fuel source for directing gaseous fuel to a combustor of the aircraft engine. The fuel swirler defines a gaseous fuel path extending from a fuel inlet to a fuel outlet. The gaseous fuel path includes a plurality of discrete apertures distributed around a circumference of the fuel swirler, each of the plurality of discrete apertures having a cross-sectional area selected to prevent a flame from propagating in an upstream direction through the gaseous fuel path towards the gaseous fuel source.

A fuel supply system for a gas turbine engine comprises a housing having a housing interior chamber and a fuel swirler disposed inside the housing interior chamber. The fuel swirler has an upstream end and downstream end relative to a fuel flow direction along a fuel nozzle longitudinal axis. The fuel swirler has a first axial fuel passage along the longitudinal axis in fluid communication with a first fuel supply and terminating at a first fuel outlet at the downstream end, a second axial fuel passage along the longitudinal axis in fluid communication with a second fuel supply and terminating at a second fuel outlet at the downstream end, and a plurality of compressed air outlets at the downstream end. The first fuel outlet is positioned on an outermost surface of the fuel swirler and leads directly to a mixing site downstream of the fuel swirler.

A burner supply tube, and a burner arrangement having such a burner supply tube, which includes a tube wall extending having a tube diameter and at least one integrated fuel channel extending from a fuel input at an upstream tube end to a fuel output at a downstream tube end. To enable an integrated design, the fuel channel is along the majority of the tube length helical with a gradient of at least 0.5 times and at most 5 times the tube diameter.

A burner supply tube, and a burner arrangement having such a burner supply tube, which includes a tube wall extending having a tube diameter and at least one integrated fuel channel extending from a fuel input at an upstream tube end to a fuel output at a downstream tube end. To enable an integrated design, the fuel channel is along the majority of the tube length helical with a gradient of at least 0.5 times and at most 5 times the tube diameter.

In a combustor including a plurality of combustion nozzles, and a gas turbine including the same, fuel can be uniformly mixed with compressed air for each combustion nozzle. The combustor includes a plurality of combustion nozzles arranged in a nozzle casing, and each combustion nozzle includes a nozzle shroud for taking in compressed air; an injection cylinder concentrically disposed in the nozzle shroud and configured to be supplied with fuel for mixing with the compressed air; and a plurality of swirlers circumferentially arranged around the injection cylinder and configured to inject the fuel from the injection cylinder into the shroud. The plurality of swirlers divide an interior space of the nozzle shroud into a plurality of fluid flow regions, and include a pair of adjacent swirlers spaced apart from each other by a circumferential distance that differs from a circumferential distance between another pair of adjacent swirlers.