Abstract: A combustor assembly for a gas turbine engine, the combustor assembly including: combustor wall defining combustion chamber and including opening periphery, the opening periphery defining first opening; sealing element including annular body, annular body extending around sealing element axis and extending through first opening, sealing element further including flange extending radially outward from annular body, flange slidingly coupling sealing element and combustor wall and forming seal or first partial seal between sealing element and combustor wall, annular body including outer and inner surface, inner surface defining second opening configured to receive fuel nozzle, wherein first total clearance between outer surface and opening periphery in first direction is greater than second total clearance between outer surface and opening periphery in second direction perpendicular to first direction such that sealing element is able to slide relative to combustor wall by greater extent in first direction than

Abstract: A combustor assembly for gas turbine engine, combustor assembly including: combustor wall including interior surface and combustor wall opening, wherein interior surface partially defines combustion chamber, wherein combustor wall opening extends between combustion chamber and its exterior; sealing element disposed partially within combustor wall opening and includes air inlet, air outlet and air passageway, wherein air outlet exits into combustion chamber and delivers flow of air received from exterior of combustion chamber via air inlet and air passageway to combustion chamber; and fuel nozzle coupled to sealing element and configured to deliver fuel into combustion chamber, wherein combustor wall further includes first bearing surface and sealing element further includes second bearing surface, wherein first bearing surface is concave and forms part of first spherical surface such that first and second bearing surfaces are configured to move relative to each other about central point of first spherical sur

Abstract: A combustion chamber (15) comprising a wall at least partially defining a combustion zone and having a first surface (41) facing away from the combustion zone and a second surface (43) facing the combustion zone, the wall having at least one effusion cooling aperture (69, 73) extending there-through from the first surface to the second surface, the effusion cooling aperture having an inlet in the first surface and an outlet in the second surface, the first surface having a particle separator (84) at least partially located upstream of the inlet of the effusion cooling aperture, the particle separator projecting away from the first surface and away from the combustion zone.

Abstract: A combustion chamber (15) comprising a wall at least partially defining a combustion zone and having a first surface (41) facing away from the combustion zone and a second surface (43) facing the combustion zone, the wall having at least one effusion cooling aperture (69, 73) extending there-through from the first surface to the second surface, the effusion cooling aperture having an inlet in the first surface and an outlet in the second surface, the first surface having a particle separator (84) at least partially located upstream of the inlet of the effusion cooling aperture, the particle separator projecting away from the first surface and away from the combustion zone.

Abstract: A fuel spray nozzle comprises a fuel passage (1) having at least one inlet and at least one outlet. The outlet is configured for accelerating fuel exiting the fuel passage into a jet. An air swirler (3) is arranged outboard of the fuel passage and converges to a single outlet chamber (5) adjacent the fuel passage outlet(s). The air swirler (3) can be nominally concentrically arranged but have some freedom to move axially or radially or change its angular position. The fuel passage outlets may be arranged symmetrically in an annular configuration. An air passage may be arranged axially within the annular array of fuel passage outlets.

Abstract: A fuel injector provided for gas turbine engine has a nozzle including pilot fuel and mains fuel discharge orifice's for respectively spraying pilot and mains fuel flows into a combustor of the engine. The injector further has a feed arm extending to the nozzle for feeding fuel to the pilot and mains discharge orifices from pilot and mains supplies respectively. The nozzle and the feed arm contain one or more pilot passages for flow of the pilot fuel flow from the pilot supply to the pilot discharge orifice and one or more mains passages for flow of the mains fuel flow from the mains supply to the mains discharge orifice. The nozzle and the feed arm contain a plurality of the pilot passages and/or a plurality of the mains passages. The pilot and the mains passages intertwine repeatedly, and are both smoothly curved as they intertwine around each other.

Abstract: An annular air swirler configured to receive a fuel injector in a central bore. The swirler has one or more annular channels, defined by radially facing channel walls and having an inlet for receiving compressed air and an axially distal outlet. The channel walls converge inwardly towards the outlet and swirl vanes extend between opposing faces of the walls. The swirler turns incoming air to create a vortex at the channel outlet. An annular cooling apparatus associated with the air swirler is arranged axially adjacently downstream of the channel outlet(s), and includes a skirt portion radially spaced from a converging portion of the outermost channel wall defining a converging portion of a bowed coolant channel. A radially outwardly extending wall connects with the outermost channel wall and, with a face of the skirt portion, defines a radially outwardly extending portion of the bowed coolant channel adapted for increased heat exchange.

Abstract: A fuel injector provided for gas turbine engine has a nozzle including pilot fuel and mains fuel discharge orifice's for respectively spraying pilot and mains fuel flows into a combustor of the engine. The injector further has a feed arm extending to the nozzle for feeding fuel to the pilot and mains discharge orifices from pilot and mains supplies respectively. The nozzle and the feed arm contain one or more pilot passages for flow of the pilot fuel flow from the pilot supply to the pilot discharge orifice and one or more mains passages for flow of the mains fuel flow from the mains supply to the mains discharge orifice. The nozzle and the feed arm contain a plurality of the pilot passages and/or a plurality of the mains passages. The pilot and the mains passages intertwine repeatedly, and are both smoothly curved as they intertwine around each other.

Abstract: 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).

Abstract: 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).

Abstract: 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.

Abstract: An annular air swirler configured to receive a fuel injector in a central bore. The swirler has one or more annular channels, defined by radially facing channel walls and having an inlet for receiving compressed air and an axially distal outlet. The channel walls converge inwardly towards the outlet and swirl vanes extend between opposing faces of the walls. The swirler turns incoming air to create a vortex at the channel outlet. An annular cooling apparatus associated with the air swirler is arranged axially adjacently downstream of the channel outlet(s), and includes a skirt portion radially spaced from a converging portion of the outermost channel wall defining a converging portion of a bowed coolant channel. A radially outwardly extending wall connects with the outermost channel wall and, with a face of the skirt portion, defines a radially outwardly extending portion of the bowed coolant channel adapted for increased heat exchange.

Abstract: A fuel spray nozzle comprises a fuel passage (1) having at least one inlet and at least one outlet. The outlet is configured for accelerating fuel exiting the fuel passage into a jet. An air swirler (3) is arranged outboard of the fuel passage and converges to a single outlet chamber (5) adjacent the fuel passage outlet(s). The air swirler (3) can be nominally concentrically arranged but have some freedom to move axially or radially or change its angular position. The fuel passage outlets may be arranged symmetrically in an annular configuration. An air passage may be arranged axially within the annular array of fuel passage outlets.