An injector for a combustor of a gas turbine engine is provided with a plurality of air/fuel mixing tubes divided into radially outer and radially inner subsets of air/fuel mixing tubes with a first fuel manifold in fluid communication with the radially outer subset of air/fuel mixing tubes and a second fuel manifold in fluid communication with the radially inner subset of air/fuel mixing tubes. A blocker is provided at an outlet portion of each of the air/fuel mixing tubes of the radially outer subset of air/fuel mixing tubes and/or the radially inner subset of air/fuel mixing tubes to form a flame anchoring surface.

A combustor assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a combustion chamber, and a fuel injector assembly in communication with the combustion chamber that has a swirler body situated about a nozzle to define an injector passage that converges to a throat. The throat is defined at a distance from the combustion chamber. The nozzle includes a primary fuel injector along a first fuel injector axis and at least one secondary plain jet fuel injector axially forward of the primary fuel injector.

A center body assembly for a lean direct injection fuel injector is disclosed. The center body assembly defines a primary liquid passage, a liquid gallery, a liquid main first passage, a liquid main second passage, and an atomizer assembly. The primary liquid passage supplies liquid fuel to the liquid gallery. The liquid gallery aligns with the primary liquid passage and distributes fuel to the liquid main first passage, and subsequently to the liquid main second passage. The atomizer assembly is in flow communication with the liquid main second passage and provides atomized fuel for combustion.

A fuel gas nozzle used in a microturbine includes a first chamber, a second chamber connected to the first chamber, a pilot fuel gas pipe, a main fuel gas pipe and an intake pipe. An intake zone and a mixing zone are respectively formed in the first chamber and the second chamber and are communicated with each other. The pilot fuel gas pipe is for introducing a first fuel gas into a downstream of the second chamber. The main fuel gas pipe is for introducing a second fuel gas into the mixing zone via the intake zone. The intake pipe is for introducing an air into the mixing zone. A centerline of the intake pipe is not intersected with a centerline of the second chamber, so as to induce a vortex flow field of the air flowing into the mixing zone for mixing the air and the second fuel gas.

A burner for a combustor of a turbomachine includes a pilot nozzle with inline premixing. The pilot nozzle is formed in an aft end of the burner. An air inlet is formed in a forward end of the burner in fluid communication with the pilot nozzle. A mixing channel extends along the axial direction between the air inlet and the pilot nozzle such that the air inlet is in fluid communication with the pilot nozzle via the mixing channel. An annular fuel plenum extends along the circumferential direction. A fuel port is in fluid communication with the annular fuel plenum and the mixing channel, the fuel port includes an outlet configured to inject fuel into the mixing channel such that a shear flow is induced.

A method, including: operating an industrial gas turbine engine having a plurality of combustor cans arranged in an annular array, each can having burner stages and a pilot burner arrangement having a premix pilot burner and a diffusion pilot burner; operating in asymmetric combustion, wherein at least one can is a warm can where respective burners stages are off and remaining cans operate as hot cans where respective burner stages are on; and while maintaining a constant rate of fuel flow to the pilot burner arrangement of the warm can, changing fuel fractions within the pilot burner arrangement of the warm can.

A gas turbine provided with: a first nozzle including a first-nozzle radially inner fuel injection hole from which to inject a first-nozzle fuel and a first-nozzle radially outer fuel injection hole which is formed on a radially outer side of the first nozzle relative to the first-nozzle radially inner fuel injection hole and upstream of the first-nozzle radially inner fuel injection hole with respect to the flow of air inside a combustor and from which to inject the first-nozzle fuel, and in a case where the first-nozzle fuel is made of a moderate calorie fuel, the first-nozzle fuel is constantly injected from the first-nozzle radially inner fuel injection hole while the gas turbine is driven, and the first-nozzle fuel is constantly injected from the first-nozzle radially outer fuel injection hole while the gas turbine is driven at a rated rotation speed.

The present invention reduces the concentration of thermal stress on a burner. A gas turbine combustor receiving compressed air from a compressor, mixing the compressed air with a fuel, burning the mixture to generate a combustion gas, and supplying the combustion gas to a turbine. The combustor includes: an inner cylinder internally forming a combustion chamber; an outer cylinder covering the inner cylinder and forming a cylindrical outer circumferential flow path between the inner and outer cylinders to allow the compressed air to flow; and a burner mounted on an end of the outer cylinder, which is positioned on an opposite side to a turbine side, and facing the combustion chamber. The burner includes a cylindrical base frame including a cavity distributing the fuel, and fuel nozzles circularly arranged as viewed from the combustion chamber and connected to the cavity. When viewed from the combustion chamber, slits extending radially are formed in the base frame such that each separate the circumferentially adjacent fuel nozzles from each other.

A mixer assembly for a gas turbine engine is provided, including a main mixer with fuel injection holes located between at least one radial swirler and at least one axial swirler, wherein the fuel injected into the main mixer is atomized and dispersed by the air flowing through the radial swirler and the axial swirler.

A fuel gas nozzle used in a microturbine includes a first chamber, a second chamber connected to the first chamber, a pilot fuel gas pipe, a main fuel gas pipe and an intake pipe. An intake zone and a mixing zone are respectively formed in the first chamber and the second chamber and are communicated with each other. The pilot fuel gas pipe is for introducing a first fuel gas into a downstream of the second chamber. The main fuel gas pipe is for introducing a second fuel gas into the mixing zone via the intake zone. The intake pipe is for introducing an air into the mixing zone. A centerline of the intake pipe is not intersected with a centerline of the second chamber, so as to induce a vortex flow field of the air flowing into the mixing zone for mixing the air and the second fuel gas.