Abstract: In a fuel injector assembly, for an internal combustion engine such as a gas turbine engine, a generally cylindrical air transfer sleeve is, in one embodiment, juxtaposed around a shroud, the sleeve having a peripheral inner recessed cavity, the outer end thereof encompassing a plurality of air inlets and the inner end thereof having a plurality of air openings connecting the cavity with tertiary air for a positive air wash, or in another embodiment, is located intermediate a fuel body and the shroud while having such inner radial dimensions so as to maintain first and second fuel/air venting gaps, with the transfer sleeve also having a peripheral outer recessed cavity wherein the inner end thereof encompasses the air inlets, with an outer end thereof being provided with a plurality of air openings, these openings connecting the recessed cavity with the first fuel/air gap downstream of a restrictor.

Abstract: A deflector at the downstream end of a fuel tube deflects incoming fuel into an annular fuel channel in a fuel swirler of an injector. The deflector prevents direct impact of the cooler fuel on the exposed walls of the swirler body. The deflector can be formed by a tab or other integral portion of the heatshield, or as a separate piece fixed to the heatshield or swirler body. The deflector minimizes disruption of flow through any flow slots that are covered by the deflector, and may have i) a relatively small circumferential extent, such that the deflector covers only a few flow slots, ii) flow openings or slots that allow a portion of the fuel to flow inwardly of the deflector into the otherwise covered flow slot(s), or iii) a space or gap between the side(s) of the deflector and the inner walls of the annular channel.

Abstract: In a fuel injector assembly, for an internal combustion engine such as a gas turbine engine, a generally cylindrical air transfer sleeve is, in one embodiment, juxtaposed around a shroud, the sleeve having a peripheral inner recessed cavity, the outer end thereof encompassing a plurality of air inlets and the inner end thereof having a plurality of air openings connecting the cavity with tertiary air for a positive air wash, or in another embodiment, is located intermediate a fuel body and the shroud while having such inner radial dimensions so as to maintain first and second fuel/air venting gaps, with the transfer sleeve also having a peripheral outer recessed cavity wherein the inner end thereof encompasses the air inlets, with an outer end thereof being provided with a plurality of air openings, these openings connecting the recessed cavity with the first fuel/air gap downstream of a restrictor.

Abstract: A fuel injector for a gas turbine engine has an inlet fitting, a fuel nozzle, and a housing stem with a pair of fuel conduits fluidly interconnecting the nozzle and fitting. The fuel nozzle includes an annular secondary fuel passageway directing fuel from one fuel conduit to an annular discharge orifice at a discharge end of the nozzle. The secondary fuel passageway is defined between an outer, annular fuel conduit portion and a primary adapter. The primary adapter has an outer surface with a distinct, radially-outwardly-projecting annular shoulder to restrict flow through the secondary passageway and provide substantially uniform distribution of flow through the passageway downstream of the shoulder, for improved combustion and flame stability.

Abstract: A deflector at the downstream end of a fuel tube deflects incoming fuel into an annular fuel channel in a fuel swirler of an injector. The deflector prevents direct impact of the cooler fuel on the exposed walls of the swirler body. The deflector can be formed by a tab or other integral portion of the heatshield, or as a separate piece fixed to the heatshield or swirler body. The deflector minimizes disruption of flow through any flow slots that are covered by the deflector, and may have i) a relatively small circumferential extent, such that the deflector covers only a few flow slots, ii) flow openings or slots that allow a portion of the fuel to flow inwardly of the deflector into the otherwise covered flow slot(s), or iii) a space or gap between the side(s) of the deflector and the inner walls of the annular channel.

Abstract: A fuel injector for a gas turbine engine has an inlet fitting, a fuel nozzle, and a housing stem with a pair of fuel conduits fluidly interconnecting the nozzle and fitting. The fuel nozzle includes an annular secondary fuel passageway directing fuel from one fuel conduit to an annular discharge orifice at a discharge end of the nozzle. The secondary fuel passageway is defined between an outer, annular fuel conduit portion and a primary adapter. The primary adapter has an outer surface with a distinct, radially-outwardly-projecting annular shoulder to restrict flow through the secondary passageway and provide substantially uniform distribution of flow through the passageway downstream of the shoulder, for improved combustion and flame stability.

Abstract: An airblast fuel nozzle has an injector head with an outer air flow through an outer air flow swirler, an intermediate fuel flow through an intermediate fuel swirler, and an inner air flow through an inner air swirler. A heatshield assembly protects the intermediate fuel swirler from hot air passing through the inner air swirler. The heatshield assembly includes an inner heatshield extending from the inlet end of the fuel swirler to the outlet end of the fuel swirler, and an intermediate heatshield disposed between the inner heatshield and the fuel swirler. According to one embodiment, the inner heatshield is connected, such as by brazing, at its downstream end to the intermediate heatshield, and at its upstream end to the fuel swirler. The upstream connection to the fuel swirler is preferably at or downstream from the midpoint of the fuel swirler. An air gap is provided between the inner heatshield and the intermediate heatshield, and between the intermediate heatshield and the fuel swirler.

Abstract: A fuel nozzle for the combustor of gas turbine engines includes evacuated radial and axial bellows concentrically mounted to the fuel passages to prevent coking of the fuel passages and maintain the structural integrity of the integral parts and particularly the weld joints and the method of construction is disclosed.