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).

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.

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.

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 flat-jet fuel injector for an aircraft turbine engine, comprising a body having a generally elongate shape having a longitudinal axis A, the body comprising a main pipe having a generally elongate shape having a longitudinal axis B substantially perpendicular to the longitudinal axis A, the two longitudinal ends of the main pipe being connected directly and respectively to longitudinal ends of two secondary pipes having a generally elongate shape having a longitudinal axis C at least substantially parallel to the longitudinal axis A, and being configured to form, respectively, two separate fuel flow inlets intended to meet substantially at the middle of the main pipe which comprises at least one ejection slot for ejecting the fuel jet, wherein at least one of the main and secondary pipes defines a flow area, at least one geometric parameter of which, such as the shape or a dimension, varies along the pipe and/or is different from the same geometric parameter defined by a flow area of another of the pipes.

A flat-jet fuel injector for an aircraft turbine engine, comprising a body having a generally elongate shape having a longitudinal axis A, the body comprising a main pipe having a generally elongate shape having a longitudinal axis B substantially perpendicular to the longitudinal axis A, the two longitudinal ends of the main pipe being connected directly and respectively to longitudinal ends of two secondary pipes having a generally elongate shape having a longitudinal axis C at least substantially parallel to the longitudinal axis A, and being configured to form, respectively, two separate fuel flow inlets intended to meet substantially at the middle of the main pipe which comprises at least one ejection slot for ejecting the fuel jet, wherein at least one of the main and secondary pipes defines a flow area, at least one geometric parameter of which, such as the shape or a dimension, varies along the pipe and/or is different from the same geometric parameter defined by a flow area of another of the pipes.

A fuel supply nozzle unit includes a fuel supply nozzle, a rear end and an end plate. The fuel supply nozzle includes a front end that has a plurality of fuel supply holes. The rear end extends from the front end and is formed with a threaded portion on its outer surface. The end plate is connected to the rear end and is formed with a plurality of threaded holes.