Abstract: Nozzle for engine has coaxial arrangement of inner pilot and outer mains airblast fuel injectors and intermediate air-swirler passage sandwiched between the outer and inner air-swirler passages of the pilot and mains airblast fuel injectors, respectively. The nozzle has an annular first-splitter wall separating the pilot outer air-swirler passage from the intermediate one. An outer surface profile of the first-splitter wall defines radially inner side of the intermediate air-swirler passage. The nozzle has an annular second-splitter wall separating the intermediate air-swirler passage from mains inner air-swirler passage. An inner surface profile of second-splitter wall defines radially outer side of intermediate air-swirler passage. The outer and inner surface profile of the first and second splitters walls, respectively, have convergent sections facing each other forming convergent portion of the intermediate air-swirler passage.

Abstract: An igniter assembly for a combustion system of a gas turbine engine is provided. The igniter assembly includes an igniter plug having a tip which, in use, is located at an aperture in a wall of a flame-tube of the combustion system such that the tip can provide an electrical discharge to ignite an air-fuel mixture within the flame-tube. The igniter assembly further includes a substantially annular igniter boss which locates on the wall of the flame-tube at the aperture to encircle the tip. The igniter boss has a slot formed therein at one side of the tip. An entrance of the slot receives air from outside the flame-tube and an exit of the slot delivers the air as a sheet-shaped flow over the tip. The slot is tapered such that the thickness of the slot narrows from its entrance to its exit.

Abstract: An airblast fuel injector for a gas turbine engine fuel spray nozzle has, in order from radially inner to outer, a coaxial arrangement of an inner air swirler passage, an annular fuel passage, an annular outer air swirler passage, and an annular shroud air swirler passage. The injector further has an annular shroud having an inner surface profile. Relative to the overall axial direction of flow through the injector the shroud inner surface profile has a convergent section followed by a divergent section, the transition of which forming a first inwardly directed annular nose. The injector further has an annular wall having an outer surface profile, and having an inner surface profile. Relative to the overall axial direction of flow through the injector the wall outer surface profile has a convergent section followed by an outwardly turning section which faces across the shroud air passage to the first nose.

Abstract: Nozzle for engine has coaxial arrangement of inner pilot and outer mains airblast fuel injectors and intermediate air-swirler passage sandwiched between the outer and inner air-swirler passages of the pilot and mains airblast fuel injectors, respectively. The nozzle has an annular first-splitter wall separating the pilot outer air-swirler passage from the intermediate one. An outer surface profile of the first-splitter wall defines radially inner side of the intermediate air-swirler passage. The nozzle has an annular second-splitter wall separating the intermediate air-swirler passage from mains inner air-swirler passage. An inner surface profile of second-splitter wall defines radially outer side of intermediate air-swirler passage. The outer and inner surface profile of the first and second splitters walls, respectively, have convergent sections facing each other forming convergent portion of the intermediate air-swirler passage.

Abstract: Nozzle for engine has coaxial arrangement of inner pilot and outer mains airblast fuel injectors and intermediate air-swirler passage sandwiched between the outer and inner air-swirler passages of the pilot and mains airblast fuel injectors, respectively. The nozzle has an annular first-splitter wall separating the pilot outer air-swirler passage from the intermediate one. An outer surface profile of the first-splitter wall defines radially inner side of the intermediate air-swirler passage. The nozzle has an annular second-splitter wall separating the intermediate air-swirler passage from mains inner air-swirler passage. An inner surface profile of second-splitter wall defines radially outer side of intermediate air-swirler passage. The outer and inner surface profile of the first and second splitters walls, respectively, have convergent sections facing each other forming convergent portion of the intermediate air-swirler passage.

Abstract: An airblast fuel injector for a gas turbine engine fuel spray nozzle has, in order from radially inner to outer, a coaxial arrangement of an inner air swirler passage, an annular fuel passage, an annular outer air swirler passage, and an annular shroud air swirler passage. The injector further has an annular shroud having an inner surface profile. Relative to the overall axial direction of flow through the injector the shroud inner surface profile has a convergent section followed by a divergent section, the transition of which forming a first inwardly directed annular nose. The injector further has an annular wall having an outer surface profile, and having an inner surface profile. Relative to the overall axial direction of flow through the injector the wall outer surface profile has a convergent section followed by an outwardly turning section which faces across the shroud air passage to the first nose.

Abstract: An igniter assembly for a combustion system of a gas turbine engine is provided. The igniter assembly includes an igniter plug having a tip which, in use, is located at an aperture in a wall of a flame-tube of the combustion system such that the tip can provide an electrical discharge to ignite an air-fuel mixture within the flame-tube. The igniter assembly further includes a substantially annular igniter boss which locates on the wall of the flame-tube at the aperture to encircle the tip. The igniter boss has a slot formed therein at one side of the tip. An entrance of the slot receives air from outside the flame-tube and an exit of the slot delivers the air as a sheet-shaped flow over the tip. The slot is tapered such that the thickness of the slot narrows from its entrance to its exit.

Abstract: An airblast fuel injector for a gas turbine engine fuel spray nozzle has, in order from radially inner to outer, a coaxial arrangement of an inner air swirler passage, an annular fuel passage, an annular outer air swirler passage, and an annular shroud air swirler passage. The injector further has an annular shroud having an inner surface profile. Relative to the overall axial direction of flow through the injector the shroud inner surface profile has a convergent section followed by a divergent section, the transition of which forming a first inwardly directed annular nose. The injector further has an annular wall having an outer surface profile, and having an inner surface profile. Relative to the overall axial direction of flow through the injector the wall outer surface profile has a convergent section followed by an outwardly turning section which faces across the shroud air passage to the first nose.

Abstract: Nozzle for engine has coaxial arrangement of inner pilot and outer mains airblast fuel injectors and intermediate air-swirler passage sandwiched between the outer and inner air-swirler passages of the pilot and mains airblast fuel injectors, respectively. The nozzle has an annular first-splitter wall separating the pilot outer air-swirler passage from the intermediate one. An outer surface profile of the first-splitter wall defines radially inner side of the intermediate air-swirler passage. The nozzle has an annular second-splitter wall separating the intermediate air-swirler passage from mains inner air-swirler passage. An inner surface profile of second-splitter wall defines radially outer side of intermediate air-swirler passage. The outer and inner surface profile of the first and second splitters walls, respectively, have convergent sections facing each other forming convergent portion of the intermediate air-swirler passage.

Abstract: An airblast fuel injector for a gas turbine engine fuel spray nozzle has, in order from radially inner to outer, a coaxial arrangement of an inner air swirler passage, an annular fuel passage, an annular outer air swirler passage, and an annular shroud air swirler passage. The injector further has an annular shroud having an inner surface profile. Relative to the overall axial direction of flow through the injector the shroud inner surface profile has a convergent section followed by a divergent section, the transition of which forming a first inwardly directed annular nose. The injector further has an annular wall having an outer surface profile, and having an inner surface profile. Relative to the overall axial direction of flow through the injector the wall outer surface profile has a convergent section followed by an outwardly turning section which faces across the shroud air passage to the first nose.

Abstract: A fuel injector includes pilot and main fuel injectors. The pilot fuel injector includes at least one pilot air swirler and the main fuel injector includes a main air blast fuel injector located between inner main and outer main air swirlers. A first air splitter is located between the pilot and inner main air swirlers and a second air splitter is located between the pilot and inner main air swirlers. The first air splitter has a downstream portion converging to a downstream end. The second air splitter has a downstream portion diverging to a downstream end. The second air splitter downstream end is downstream of the first air splitter downstream end and the ratio of the distance from the first air splitter downstream end to the second air splitter downstream end to the diameter of the second air splitter downstream end is in the range of 0.22 to 0.30.

Abstract: A fuel injector for a fuel spray nozzle of a gas turbine engine combustor is provided. The fuel injector has an annular flow passage which conveys fuel to a prefilming lip at an end of the flow passage. The fuel injector also has plurality of fuel distributor slots which are circumferentially spaced around and in fluid communication with the other end of the flow passage to deliver respective fuel streams into the flow passage. The slots are configured so that the fuel streams enter the flow passage at a swirl angle of at least 80° relative to the axis of the flow passage.

Abstract: A fuel injector for a fuel spray nozzle of a gas turbine engine combustor is provided. The fuel injector has an annular flow passage which conveys fuel to a prefilming lip at an end of the flow passage. The fuel injector also has plurality of fuel distributor slots which are circumferentially spaced around and in fluid communication with the other end of the flow passage to deliver respective fuel streams into the flow passage. The slots are configured so that the fuel streams enter the flow passage at a swirl angle of at least 80° relative to the axis of the flow passage.

Abstract: An ejector, which finds particular application as a fuel injector for a gas turbine engine, has an axially located passage ending as a nozzle having an internal surface facing radially inwardly towards the axis and which extends as an outboard cone about the axis of the passage and which terminates at a tip. The cone has a profile which replicates the unconstrained trajectory of the fuel leaving the passage. The outer surface of the ejector has a profile for accelerating a gaseous flow over the outer surface. Atomisation of fuel is improved along with relight capability, flame extinction and smoke production.