A fuel injector for an aircraft gas turbine engine includes a housing stem, a fuel nozzle coupled to the housing stem, and a fuel conduit extending through the housing stem and into the fuel nozzle where the fuel conduit bends to extend in a longitudinal downstream direction within the fuel nozzle. The fuel conduit is configured to transport bulk fuel flow further along the nozzle before being split downstream in the fuel circuit for final spray distribution, thereby promoting lower fuel temperatures. The fuel nozzle may minimize metal-to-metal contact between an external wall of the nozzle in thermal communication with ambient environment and an internal portion of the nozzle in thermal communication with the fuel circuit to minimize heat pick-up in the fuel. The fuel conduit may include a coiled section within a cavity of the fuel nozzle for compensating for thermal growth mismatches of the fuel injector.

A burner comprises: at least one mixing tube extending inside a fuel plenum and having an interior configured to be supplied with an air; and a plurality of fuel injection holes for injecting a fuel supplied to the fuel plenum into the interior of the at least one mixing tube. When the at least one mixing tube is viewed in an axial direction of the mixing tube, a central axis of each of the plurality of fuel injection holes is oblique in a same direction with respect to a circumferential direction of the mixing tube, to a radial direction of the mixing tube.

An atomizing burner and corresponding method for turning an atomizing burner from an ON state to an OFF state. The burner has independently controllable flows of atomizing air, combustion air, and fuel flow, the burner in the ON state having flow values of burner parameters including flow of atomizing air, flow of combustion air, and fuel flow. The method includes: changing, in response to an OFF instruction, flow of at least one of the flow of atomizing air, combustion air and/or fuel to a lower non-zero value; first discontinuing, after a first period of time since the changing, flow of fuel and flow of atomizing air; maintaining, for a second period of time since the first period of time, flow of combustion air; second discontinuing, after the maintaining, flow of combustion air; wherein the maintaining prevents buildup of excess heat inside the burner during the transition to the OFF state.

An atomizing burner and corresponding method for turning an atomizing burner from an ON state to an OFF state. The burner has independently controllable flows of atomizing air, combustion air, and fuel flow, the burner in the ON state having flow values of burner parameters including flow of atomizing air, flow of combustion air, and fuel flow. The method includes: changing, in response to an OFF instruction, flow of at least one of the flow of atomizing air, combustion air and/or fuel to a lower non-zero value; first discontinuing, after a first period of time since the changing, flow of fuel and flow of atomizing air; maintaining, for a second period of time since the first period of time, flow of combustion air; second discontinuing, after the maintaining, flow of combustion air; wherein the maintaining prevents buildup of excess heat inside the burner during the transition to the OFF state.

A main fuel injector of a fuel injection device includes: a main outer air passage including an inlet that is open outward in a radial direction, the main outer air passage taking in compressed air through the inlet; a main inner air passage including an inlet that is open inward in the radial direction, the main inner air passage taking in the compressed air through the inlet; a merged air passage, in which the compressed air taken in by the main outer air passage and the compressed air taken in by the main inner air passage merge together; and a main fuel injection port configured to inject a fuel into the compressed air taken in by the main outer air passage or into the compressed air taken in by the main inner air passage.

A flow directing apparatus for directing fluid flow includes a flow body defining a bore therethrough configured and adapted to direct fluid flowing therethrough. The bore includes an outlet and an opposed inlet with an enlargement, formed as a countersink and/or a chamfer using a suitable boring device. The enlargement is configured and adapted to reduce sensitivity to entrance-edge conditions for the bore.

Flow blurring injection utilizes a two-phase concept to generate fine sprays immediately at the interior exit, rather than a typical jet which gradually disintegrates into ligaments and then finer droplets for a conventional injector. Therefore, clean combustion is achieved with the FB injection for fuels with distinct properties without fuel preheating or hardware modification. However, in addition to the droplets, the FB injection also produces ligaments for highly viscous liquids and relatively larger droplets at spray edge, resulting in difficulty in sustaining the flame and performs incomplete combustion and higher emissions close to the combustor all. The disclosed swirl burst injector and method utilizes the advantages of FB injection and swirl atomization to further improve atomization, and overcomes the limitations of FB injection, providing a sustainable way to use both conventional and alternative fuels with improved efficiency and minimized emissions. The fine atomization of the present invention can be also used in various applications where fine sprays are needed.

A fluid-gas mixer including a housing, defining a primary axis, for mixing fluid and gas, a mixer nozzle circumscribing the primary axis, wherein an annular gap between an outer surface of the mixer nozzle and an inner surface of the housing defines at least one outer gas path, a swirling gas passage defining an inner gas path for mixing with the outer gas path.

The present disclosure is directed to systems and methods for low-CO.sub.2 emission combustion of liquid fuel with a gas-assisted liquid fuel oxygen reactor. The system comprises an atomizer that sprays fuel and CO.sub.2 into an evaporation zone, where the fuel and CO.sub.2 is heated into a vaporized form. The system comprises a reaction zone that receives the vaporized fuel and CO.sub.2. The system includes an air vessel having an air stream, and a heating vessel adjacent to the air vessel that transfers heat to the air vessel. The system comprises an ion transport membrane in flow communication with the air vessel and reaction zone. The ion transport membrane receives O.sub.2 permeating from the air stream and transfers the O.sub.2 into the reaction zone resulting in combustion of fuel. The combustion produces heat and creates CO.sub.2 exhaust gases that are recirculated in the system limiting emission of CO.sub.2.

The present disclosure is directed to systems and methods for low-CO.sub.2 emission combustion of liquid fuel with a gas-assisted liquid fuel oxygen reactor. The system comprises an atomizer that sprays fuel and CO.sub.2 into an evaporation zone, where the fuel and CO.sub.2 is heated into a vaporized form. The system comprises a reaction zone that receives the vaporized fuel and CO.sub.2. The system includes an air vessel having an air stream, and a heating vessel adjacent to the air vessel that transfers heat to the air vessel. The system comprises an ion transport membrane in flow communication with the air vessel and reaction zone. The ion transport membrane receives O.sub.2 permeating from the air stream and transfers the O.sub.2 into the reaction zone resulting in combustion of fuel. The combustion produces heat and creates CO.sub.2 exhaust gases that are recirculated in the system limiting emission of CO.sub.2.