A combustion system such as a furnace or boiler includes a perforated reaction holder configured to hold a combustion reaction that produces very low oxides of nitrogen (NOx).

An arrangement for an aircraft turbine engine combustion chamber including an injection system and a fuel injector is provided. The injection system includes an injector nozzle guide, the inner surface of which delimits an opening for centering the nozzle, which includes an outer casing. The arrangement further includes a sealing device between the inner surface of the guide and the outer casing. The sealing device includes a first part accommodated in a groove of the outer casing, the groove being delimited, in part, by a downstream delimiting surface, the first part having a first sealing surface and bearing axially against the downstream delimiting surface; and a second part having a second sealing surface bearing radially against the inner surface of the guide.

A fuel injection system may comprise a mixer and a fuel injector disposed within the mixer. The mixer may comprise an outer housing with an exit port and a bluff body extending across the exit port of the outer housing. A flared surface of the mixer may match a contour of the bluff body.

A nozzle for injecting liquid includes a nozzle body defining a flow channel and a swirl ante-chamber in fluid communication with the flow channel. An injection point orifice is defined in the swirl ante-chamber. The flow channel feeds into the swirl ante-chamber to impart a tangential flow component on fluids entering the swirl ante-chamber to generate swirl on a spray issuing from the injection point orifice. A second flow channel can be included in fluid communication with the swirl ante-chamber. The second flow channel feeds into the swirl ante-chamber in cooperation with or in opposition to the first flow channel. The first flow channel, second flow channel, and swirl ante-chamber are configured and adapted to adjust spray angle of a spray issuing from the injection point orifice by varying flow apportionment among the first and second flow channels.

The present disclosure relates to a liquid fuel self-sustaining combustion burner for flame synthesis, including a swirl-flow cylinder and a stable combustion cylinder. A swirl-flow plate is disposed at an open end of the swirl-flow cylinder and defines swirl-flow outlets. A tangential inlet tube is mounted on the swirl-flow cylinder and in fluid communication with the swirl-flow chamber. An open end of the swirl-flow cylinder extends into the stable combustion chamber. The fuel can be atomized by an atomizer and sprayed into the stable combustion chamber for combustion. Air introduced from the tangential inlet tube can flow into the swirl-flow chamber and advance spirally around the central stabilizing column to reach the swirl-flow plate. The airflow is partially injected into the stable combustion chamber through the swirl-flow outlets, and then continues to spirally advance. An atomizing nozzle of the atomizer is located inside the swirling airflow.

A turbine engine can include a compressor section, a combustion section, and a turbine section in serial flow arrangement. The combustion section can include a combustor with a fuel premixer. The fuel premixer can include an annular shroud defining an interior, a center body located within the interior, and an annular swirler located within the interior.

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.

A swirler-ferrule assembly includes a radial swirler, a ferrule, a fuel nozzle, and a surface feature. The radial swirler includes a primary swirler vane having a primary air passage and a secondary swirler vane having a secondary air passage. The ferrule may be connected to the radial swirler. The surface feature may be located on the primary swirler vane and/or the ferrule. The surface feature may be configured to direct an air flow through the primary air passage away from a recirculation zone located upstream of the primary swirler vane. The surface feature has a trailing end and a distal end, and the fuel nozzle is axially aligned with the trailing end of the surface feature or is located axially downstream of the trailing end of the surface feature. The surface feature may have a plurality of grooves.

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 liquid fuel injector includes a cylindrical center body including a center axis, an annular shroud concentrically disposed outside the center body, an annular fuel injection body disposed between and concentrically with the center body and the shroud, and including a fuel passage formed therein, a plurality of inner swirl vanes that are arranged in an equal cycle in an inner air passage between the center body and the fuel injection body, and are provided with an inner swirl vane action surface on an upstream side, a plurality of outer swirl vanes that are arranged in an equal cycle in an outer air passage between the fuel injection body and the shroud, and an outer swirl vane action surface on the upstream side.