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 fuel injector for a turbomachine includes an outer heat shield configured to sit on and/or within a combustor dome to orient the fuel injector relative to the combustor dome and/or a fuel manifold. An inner surface of the outer heat shield includes an outer heat shield seal surface. The injector also includes a fuel prefilmer seated at least partially within the outer heat shield. An outer surface of the fuel prefilmer includes a prefilmer seal surface configured to mate with the outer heat shield seal surface such that the fuel prefilmer seats on the outer heat shield seal surface and such that the prefilmer seal surface is configured to allow the surfaces to slide relative to one another in both a radial and axial direction.

A gas turbine combustor assembly includes a fuel injector, a dome stator around the fuel injector, and a dome sleeve coupled to the dome stator. The dome sleeve defines an air inlet opening with the dome stator, and is carried to move with respect to the dome stator to change a flow area of the air inlet opening. The dome sleeve also defines a nozzle sloping downstream from the air inlet opening toward an outlet of the combustor assembly. The sloping nozzle defines an annular pinch gap adjacent an outlet of the fuel injector, and is coupled to move with the dome sleeve to change a flow area through the pinch gap.

A conduit for transport of a fluid, the conduit comprising: a wall extending around and along an axis extending parallel to a direction of bulk fluid flow. The wall having an inner surface defining an interior of a channel through which fluid flows; and a plurality of projections extending from the inner surface of the wall. The plurality of projections extend around the axis, in a plane perpendicular to the axis; and wherein the projections have a height perpendicular to the axis into the channel, and the height is arranged such that the projections modify the flow of fluid at a boundary layer of the fluid adjacent the wall. The conduit is arranged to carry a first fluid; the conduit includes an opening for introducing a second fluid into the channel such that the first and second fluid are mixed downstream of the opening and the plurality of projections are provided upstream of the opening, in a direction of fluid flow.

An assembly includes an injection system and an injector for an aircraft turbomachine combustion chamber. The system includes an aerodynamic bowl including a first end widening toward the downstream end and centered on a central axis of the injection system, this also including a central body along which a film of fuel is intended to flow in the downstream direction. The central body includes a second end widening toward the downstream end, the first and second widening ends between them delimiting an air through duct and the system includes motion inducing a device allowing a relative movement between the first widening end which is stationary and the second widening end, along the central axis of the injection system, by moving the central body relative to the injector.

A method for delivering fuel from a fuel nozzle of a combustor of a gas turbine engine includes directing fuel from a fuel source through a flow splitter to provide at least two concentric fuel flows, filming the concentric two fuel flows on concentrically arranged inwardly facing filming surfaces that are disposed downstream of the flow splitter, and atomizing the concentric fuel flows into a core air flow.

A fuel injector includes a feed arm with an inlet end and a nozzle body extending from the feed arm at an end opposite the inlet end. The nozzle body defines a prefilming chamber that opens into an annular outlet orifice for issuing a spray therefrom. A plurality of fuel circuits is defined from the inlet end of the feed arm to the prefilming chamber of the nozzle body. Each fuel circuit in the plurality of fuel circuits can include a single respective inlet opening at the inlet end of the feed arm, with a single respective conduit extending through the feed arm and nozzle body from the single respective inlet opening to a single respective outlet slot feeding into the prefilming chamber.

A method of delivering fuel from a fuel nozzle of a gas turbine engine includes carrying by a fuel passageway of the fuel nozzle a film of pressurised fuel, the fuel passageway being disposed radially outwardly from an air passageway carrying a flow of pressurised air, and directing the film of pressurised fuel onto an inside surface of an exit lip of an outer wall of the fuel passageway and thinning the film of pressurised fuel as it travels therealong. The exit lip generally increases in diameter as it extends downstream.

A fuel injection system for use in a combustor of a turbine engine includes a mixer assembly including a mixer housing and a fuel nozzle assembly positioned radially inward of the mixer housing. The fuel nozzle assembly includes a substantially annular fuel injection housing and a substantially annular main fuel injector coupled to the fuel injection housing. The main fuel injector includes a body, a fuel delivery passage defined in the body, a swirl chamber defined in the body downstream of the fuel delivery passage, and a plurality of circumferentially-spaced fuel metering slots defined in the body and coupled in flow communication with and between the fuel delivery passage and the swirl chamber.

A nozzle includes a nozzle body defining a longitudinal axis and including a primary distributor and a secondary distributor. The primary distributor has an inner air passage fed by a radial swirler; a first fuel circuit radially outboard from the inner air passage with respect to the longitudinal axis; a second fuel circuit radially outboard from the first fuel circuit with respect to the longitudinal axis, wherein each of the first fuel circuit and the second fuel circuit extends from a respective fuel circuit inlet to a respective annular fuel circuit outlet; and an outer air passage defined between a fuel circuit outer wall and an outer air passage wall, wherein the outer air passage is a converging non-swirling outer air passage. The secondary distributor similar to the primary distributor is downstream of the primary distributor with respect to the longitudinal axis.