A nozzle for injecting liquid includes a nozzle body defining a plurality of injection point orifices and an annular prefilmer positioned downstream of the injection point orifices for prefilming impingement of spray from the injection point orifices on the prefilmer. A swirl antechamber can be defined upstream of the injection point orifices for supplying a swirling liquid flow to the injection point orifices for impingement of a swirling flow on the prefilmer.

An engine can utilize a combustor to combust fuel to drive the engine. A fuel nozzle assembly can supply fuel to the combustor for combustion or ignition of the fuel. The fuel nozzle assembly can include a swirler and a fuel nozzle to supply a mixture of fuel and air for combustion, which can supply a primary fuel supply and a secondary fuel supply. Increasing efficiency and reducing emission require the use of alternative fuels, which combust at higher temperatures or burn at faster burn speeds than traditional fuels, requiring improved fuel introduction without the occurrence of flame holding or flashback.

A fuel injector for a fuel spray nozzle of a gas turbine engine combustor includes an angular lip axially projecting into an upstream section of an annular passage to guide a fuel layer vortex to flow along a radially outer passage wall of the annular passage and to guide an air layer vortex to fill into and pass through an annular space between the fuel layer vortex and a radially-inner passage wall of the annular passage. The air layer vortex is free of mixing with the fuel layer vortex before the fuel layer vortex is discharged from the annular passage for fuel atomization.

A fuel injector comprises one or more elongate fuel passages (802) having an elongate axis extending from an upstream inlet end to a downstream outlet end. One or more outlets (803) are provided at the outlet end and extend obliquely with respect to the elongate axis. The elongate fuel passage is defined by an inner skin of a double skinned pipe, the double skinned pipe defining a first annular cavity (804) between the inner skin and outer skin. The inner skin and the outer skin converge adjacent the one or more outlets (803) to form a nose (808). A bridge is arranged within the fuel passage (802) and upstream of the nose (808), the bridge comprising a plurality of arms (811) extending radially from a centre (812) to a wall of the fuel passage (802), the centre (812) arranged in axial alignment with a centre of the nose (808).

A fuel injector comprises an elongate fuel passage (31) having an elongate axis (31a) extending from an upstream inlet end to a downstream outlet end. A plurality of outlets (33) is arranged at the outlet end, each outlet extends obliquely with respect to the elongate axis (31a). The elongate fuel passage is defined by an inner skin of a double skinned pipe, the double skinned pipe defines a first annular cavity (34) between the inner skin and an outer skin. The inner skin and the outer skin meet adjacently upstream of the one or more outlets to close an end of the first annular cavity (34). The injector has a nose section (32) at a downstream end, the nose section (32) being convergent and fluted. The flutes (38) are arranged between the outlets (33) and extend towards the downstream end of the nose section (32) whereby to guide an air stream (A) passing over the injector (30) to form single jet at the downstream end of the nose section (32).

A fuel injector comprises an elongate fuel passage (38) having an elongate axis extending from an upstream inlet end to a downstream outlet end. One or more outlets (38a) at an end of the passage extend obliquely with respect to the elongate axis. The elongate fuel passage is defined by an inner skin (35a) of a double skinned pipe, the double skinned pipe defining a first annular cavity (39) between the inner skin (35a) and outer skin (35). The inner skin (35a) and the outer skin (35) meet adjacent the one or more outlets (38a) to close an end of the first annular cavity (39). A second annular cavity (40) is defined by an annular outer wall (40a) extending from downstream of the passage end to a position downstream of the one or more outlets (38a). The fuel passage outlets (38a) emerge at a radially outer surface of the annular outer wall (40a). The annular outer wall (40a) is convergent at a downstream end whereby to define an orifice (40b) centred nominally coincident with the elongate axis. The annular outer wall (40a) may form part of an annular air swirler arranged nominally concentrically on the elongate axis.

An electric motor assisted airblast injector design for gas turbines is disclosed. The electric motor assisted airblast injector assembly consists of an airblast injector, a high speed electric motor and a compressor. The electric motor assisted airblast injector is designed to improve engine light-off and starting reliability without using a fuel staging system to incorporate pressure injectors. A high speed motor is activated during starting to drive a compressor for locally producing pressurized air without sacrificing combustor performance. The pressurized air exiting the air swirler with high velocity penetrates perpendicularly into the fuel spray cone obtained by orifices in the fuel swirler. The amount of pressurized air through the compressor is controlled by motor speed to match fuel starting schedule and produce fuel/air mixture within flammability limits. After engine starting, the high speed motor may cut off as sufficient air pressure differential is available across the combustor.

A fuel nozzle apparatus for a gas turbine engine includes: a first pilot fuel injector disposed on a centerline axis of the fuel nozzle which defines a direction of air flow through the fuel nozzle, the first pilot fuel injector being of a pressure atomizing type; an annular second pilot fuel injector at least partially surrounding the first pilot fuel injector, the second pilot fuel injector being of an air blast type and having a fuel outlet disposed axially downstream and radially outboard of the first pilot fuel injector; an annular venturi surrounding the first and second pilot fuel injectors, the venturi including a throat of minimum diameter; an array of inner swirl vanes extending between the first pilot fuel injector and the second pilot fuel injector; and an array of outer swirl vanes extending between the second pilot fuel injector and the venturi.

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.

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.