A fuel nozzle for a combustor of a gas turbine engine includes an outer air swirler along an axis, said outer air swirler defines an outer annular air passage between an outer wall and an inner wall, the outer wall defines a convergent-divergent nozzle. An inner air swirler along the axis to define an annular liquid passage therebetween, the annular liquid passage terminates upstream of the convergent-divergent nozzle and an annular fuel gas passage around the axis between the outer air swirler and the inner air swirler.

An injector nose for a turbomachine includes a primary fuel circuit terminated by a fuel ejection nozzle defining an injection axis (44), and a secondary fuel circuit (64) comprising a secondary fuel swirler (114) formed of swirler channels (112) opening into a terminal fuel ejection portion (68) of annular shape arranged around the fuel ejection nozzle. Each swirler channel (112) has a passage section which decreases in a direction going from an upstream end (111) to a downstream end (115) of the swirler channel (112). The reduction of the passage section of the swirler channels (112) makes it possible to increase the head loss between the inlet and the outlet of the secondary fuel swirler (114) and thus notably to accelerate the fuel within the secondary fuel swirler, while allowing lower fuel flow rates.

A fuel spray nozzle including a primary atomizer to discharge a flow of swirled atomised fuel along and around a fuel spray nozzle axis. The primary atomiser includes outer air swirler disposed radially outwardly of a fuel pre-filmer channel. A secondary atomiser disposed around the primary atomiser includes secondary inner air swirler to swirl flow along an inner air channel. The secondary inner air swirler disposed radially inwardly of a secondary fuel pre-filmer channel of the secondary atomiser. A primary outer air channel defined between the primary outer swirler and the secondary inner swirler. The secondary inner air swirler include splitter wall to separate swirling flow in the secondary inner channel from the primary flow of atomised fuel. The secondary inner air swirler includes primary cap wall integral with and extending radially inwardly from the splitter wall to direct flow from the primary outer channel inwardly towards the fuel spray.

A turbine combustor assembly includes a fuel/air mixer assembly having a plurality of fuel/air mixer elements and a fuel injector coupled to the fuel/air mixer assembly. Each of the fuel/air mixer elements includes: a fuel/air mixer body having an internal cavity extending axially between an air inlet and an air outlet; and a prefilmer residing within an interior cavity of the fuel/air mixer body, the prefilmer including an axial inner air flow passage extending coaxially with an axial centerline of the internal cavity of the fuel/air mixer body and a radial fuel injection port into the air flow passage. The fuel injector is arranged to direct fuel into a plurality of the fuel/air mixer elements via the fuel injection port of the prefilmer of each fuel/air mixer element.

A gas turbine engine fuel nozzle comprises a spray tip defining a fuel exit passage therethrough that extends along a central axis. The fuel exit passage has an exit orifice aligned with the central axis. The exit orifice is circumscribed by an inner annular surface. The inner annular surface has a spherically-convex profile in cross-section, the profile being constant around the circumference of the inner annular surface.

A nozzle includes a nozzle body with an inner air passage fed by a first radial swirler and a second radial swirler axially downstream of the first radial swirler. A first fuel circuit is axially between the first and second radial swirlers. A second fuel circuit is axially downstream of the second radial swirler, 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. An outer air passage is defined between a fuel circuit outer wall of the second fuel circuit and an outer air passage wall, wherein the outer air passage is a converging non-swirling air passage. An intermediate air passage can be defined between an intermediate wall and the second radial swirler, wherein the intermediate air passage is a converging non-swirling air passage.

A fuel injection nozzle for a combustion turbine engine has thermal stress-relief vanes, which accommodate and relieve localized thermal stresses within its monolithic, three-dimensional nozzle structure, imparted by heat transfer during engine combustion. At least one first vane is coupled to opposing, spaced nozzle sleeves at both ends. At least one cantilever-like second vane is coupled to one of the opposing sleeves on one end, while the other free or floating end is spaced by a second vane gap from the other opposing sleeve. Some embodiments include a plurality of second vanes, which have locally varying orientation, and/or structure, and/or second vane gaps, for normalizing spatially and/or temporally thermal stresses within the nozzle structure. The monolithic structure is fabricated, in some nozzle embodiments, by additive manufacturing.

A pre-film liquid fuel cartridge (20) includes a primary liquid fuel passage (106), a plurality of inner fuel ports (116) and a plurality of outer fuel ports (124) that are in fluid communication with the primary liquid fuel passage. An inner pre-filming surface (142) is defined downstream from the plurality of inner fuel ports. The inner pre-filming surface (142) terminates at a first shear edge (140). An outer pre-filming surface (152) is defined downstream from the plurality of outer fuel ports. The outer pre-filming surface (152) terminates at a second shear edge (154). The first and second shear edges are relatively oriented so that a first pre-filmed liquid fuel sheet exiting the first shear edge intersects with a second pre-filmed liquid fuel sheet exiting the second shear edge, thereby atomizing the first and second pre-filmed liquid fuel sheets.

Provided is a liquid fuel injection body capable of further reducing a film thickness of an injected liquid fuel. A liquid fuel injection body includes: an annular fuel passage extending in an axial direction and provided inside the liquid fuel injection body, the fuel passage is defined by a fuel passage outer wall located outward in a radial direction and a fuel passage inner wall located inward in the radial direction, a plurality of throttle passages disposed discretely in a circumferential direction are provided at a portion of the fuel passage on an upstream side with respect to a downstream end of the fuel passage, each of the throttle passages is defined by a throttle passage outer wall located outward in the radial direction and formed as a cylindrical surface, a throttle passage inner wall located inward in the radial direction, and two throttle passage side walls connecting end portions of the throttle passage outer wall and the throttle passage inner wall in the circumferential direction, and the throttle passage outer wall and the fuel passage outer wall are flush whereas the throttle passage inner wall and the fuel passage inner wall are not flush.

An assembly is provided which includes a swirler and a fuel nozzle. The swirler includes an outer wall, an inner wall, an outer passage and an inner passage. The outer wall circumscribes the inner wall and extends axially along an axis to a distal outer wall end. The inner wall extends axially along the axis to a distal inner wall end that is axially recessed within the swirler from the distal outer wall end. The outer passage is radially between the inner wall and the outer wall. The inner passage is radially within the inner wall. The fuel nozzle projects into the inner passage. The fuel nozzle includes a plurality of fuel outlets and a plurality of air outlets. The fuel outlets are axially aligned with the inner wall. The air outlets are axially upstream of and radially outboard of the fuel outlets.