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 centred 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 fuel nozzle device for a gas turbine engine includes a nozzle body extending in an axial direction and projecting into the combustion chamber, and swirler including a tubular portion concentrically surrounding the nozzle body, a deflector formed as a hollow shell concentrically surrounding the tubular portion, and a plurality of swirl vanes extending between the tubular portion and the deflector. Each swirl vane extends along a logarithmic spiral around an axial center of the nozzle body between the tubular portion and the deflector with a certain meridian crossing angle α and a certain twist angle Φ such that the outer peripheral inclination angle θ is smaller than the stacking angle β of the swirl vane when the swirl vane is manufactured by an additive manufacturing process with a front end up orientation.

An energy extraction system according to an exemplary embodiment of this disclosure, among other possible things includes an ammonia fuel storage tank assembly that is configured to store a liquid ammonia fuel, a thermal transfer assembly that is configured to transform the liquid ammonia fuel into a vaporized ammonia based fuel, a turbo-expander that is configured to expand the vaporized ammonia based fuel to extract work, and an energy conversion device that is configured to use the vaporized ammonia based fuel from the turbo-expander to generate a work output.

An energy extraction system according to an exemplary embodiment of this disclosure, among other possible things includes an ammonia fuel storage tank assembly that is configured to store a liquid ammonia fuel, a thermal transfer assembly that is configured to transform the liquid ammonia fuel into a vaporized ammonia based fuel, a turbo-expander that is configured to expand the vaporized ammonia based fuel to extract work, and an energy conversion device that is configured to use the vaporized ammonia based fuel from the turbo-expander to generate a work output.

A regeneration cooler (2) includes a passage forming structure (10) in which a fuel passage (11) is formed for liquid fuel to be supplied. A coating (12, 12A) is formed in the fuel passage (11) to at least partially cover a wall surface of the fuel passage (11). The coating (12, 12A) contains metal particles (13) adhered and fixed to the wall surface (11a) of the fuel passage (11) and a coating material (14, 17).

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.

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.

A low-pollution combustor and a combustion control method therefor. The low-pollution combustor includes a combustor head including a primary combustion stage and a precombustion stage, the primary combustion stage including a primary-combustion-stage channel and a primary-combustion-stage swirler disposed in the primary-combustion-stage channel. The primary combustion stage includes a pre-film plate disposed in the primary-combustion-stage channel, and the pre-film plate is radially divided into an outer-layer pre-film plate and an inner-layer pre-film plate. The positions and injection directions of fuel jet points of the primary combustion stage control fuel of the primary combustion stage to be injected into the primary-combustion-stage channel through primary-combustion-stage fuel jet orifices; and part of the fuel directly forms primary-combustion-stage direct-injection fuel spray, and the other part is hit on the pre-film plate close to an inner side of the primary-combustion-stage channel, or the two parts are respectively hit on the two layers of pre-film plates.

A low-pollution combustor and a combustion control method therefor. The low-pollution combustor includes a combustor head including a primary combustion stage and a precombustion stage, the primary combustion stage including a primary-combustion-stage channel and a primary-combustion-stage swirler disposed in the primary-combustion-stage channel. The primary combustion stage includes a pre-film plate disposed in the primary-combustion-stage channel, and the pre-film plate is radially divided into an outer-layer pre-film plate and an inner-layer pre-film plate. The positions and injection directions of fuel jet points of the primary combustion stage control fuel of the primary combustion stage to be injected into the primary-combustion-stage channel through primary-combustion-stage fuel jet orifices; and part of the fuel directly forms primary-combustion-stage direct-injection fuel spray, and the other part is hit on the pre-film plate close to an inner side of the primary-combustion-stage channel, or the two parts are respectively hit on the two layers of pre-film plates.

An atomizer provides a high-quality fuel-air mixture to a gas turbine engine, by combining air input from an engine compressor and fuel input from a single low-pressure fuel supply pump. The atomizer includes an atomizer body, a main vortex chamber, a secondary vortex chamber for improving quality of the fuel-air mixture, and a fuel sleeve providing fuel to the secondary vortex chamber. The main vortex chamber includes a main outlet nozzle in fluid communication with a combustion chamber inlet of the gas turbine engine. The secondary vortex chamber includes a secondary outlet nozzle in fluid communication with the main vortex chamber. The fuel sleeve has a blind channel with a longitudinal axis and a fuel tip. The same atomizer may be used for startup mode and for all operational modes of the gas turbine engine.