A swirler assembly of a combustor of a gas turbine, the swirler assembly including a primary swirler having a primary swirler flow opening, and a swirler ferrule plate connected to an upstream side of the primary swirler. The swirler ferrule plate includes (a) a fuel nozzle opening, and (b) a plurality of oxidizer purge passages surrounding the fuel nozzle opening, each one of the plurality of oxidizer purge passages including (i) an inlet passage portion, and (ii) an outlet passage portion extended from the inlet passage portion to a downstream end of the swirler ferrule plate and having an outlet in fluid communication with the primary swirler flow opening. The outlet passage portion has an increasing cross-sectional area extending along the length of the outer passage portion from the inlet passage portion to the outlet that induces a pressure drop in a flow of oxidizer through the oxidizer flow passage.

The present disclosure relates to a liquid fuel self-sustaining combustion burner for flame synthesis, including a swirl-flow cylinder and a stable combustion cylinder. A swirl-flow plate is disposed at an open end of the swirl-flow cylinder and defines swirl-flow outlets. A tangential inlet tube is mounted on the swirl-flow cylinder and in fluid communication with the swirl-flow chamber. An open end of the swirl-flow cylinder extends into the stable combustion chamber. The fuel can be atomized by an atomizer and sprayed into the stable combustion chamber for combustion. Air introduced from the tangential inlet tube can flow into the swirl-flow chamber and advance spirally around the central stabilizing column to reach the swirl-flow plate. The airflow is partially injected into the stable combustion chamber through the swirl-flow outlets, and then continues to spirally advance. An atomizing nozzle of the atomizer is located inside the swirling airflow.

A liquid fuel lance for a burner of a combustor of a gas turbine combustor, a liquid fuel system incorporating the liquid fuel lance and a method of operating the liquid fuel system. The liquid fuel lance has an elongate liquid fuel lance body and a liquid fuel tip. The elongate liquid fuel lance body includes a fuel flow passage and at least a first air passage and a second air passage. A liquid fuel tip defines a fuel outlet and arranged about the fuel outlet at least a first outlet and a second outlet to which air is independently supplied by the first air passage and the second air passage respectively, and wherein the amount of air supplied to the first air passage is variable.

The disclosure is directed to a swirler body for a combustor of a gas turbine engine, where the swirler body includes an annular mount face which defines at least one pocket. The disclosure is directed to a swirler assembly for a combustor of a gas turbine engine, where the swirler assembly includes a swirler first body with an annular first mount face which defines at least one first pocket and a swirler second body with an annular second mount face which abuts said annular first mount face, where said second annular mount face defines at least one second pocket. The disclosure is directed to a method of lightening a swirler assembly for a combustor of a gas turbine engine, where the method includes defining at least one pocket within an annular mount face of a swirler body.

Fuel spray nozzle for generating a spray of atomised liquid fuel in a combustor of a gas turbine engine. The nozzle includes a flow circuit that has in flow series: a gallery that receives fuel flow, plural circumferentially-spaced restrictor passages arranged in a row around the nozzle, plural conditioning passages configured to impart a circumferential component to their respective portions of the fuel flow, and an annular spin chamber which forms a swirling fuel flow which is discharged at an exit port. The restrictor passages form flow restrictions which in use produce a pressure differential between the gallery and the spin chamber to evenly circumferentially distribute the fuel flow between the restrictor passages. The conditioning passages have increased flow cross-sectional areas relative to the flow cross-sectional areas of the restrictor passages, such that the restrictor passages produce substantially all of the pressure differential between the gallery and the spin chamber.

Fuel spray nozzle for generating a spray of atomised liquid fuel in a combustor of a gas turbine engine. The nozzle includes a flow circuit that has in flow series: a gallery that receives fuel flow, plural circumferentially-spaced restrictor passages arranged in a row around the nozzle, plural conditioning passages configured to impart a circumferential component to their respective portions of the fuel flow, and an annular spin chamber which forms a swirling fuel flow which is discharged at an exit port. The restrictor passages form flow restrictions which in use produce a pressure differential between the gallery and the spin chamber to evenly circumferentially distribute the fuel flow between the restrictor passages. The conditioning passages have increased flow cross-sectional areas relative to the flow cross-sectional areas of the restrictor passages, such that the restrictor passages produce substantially all of the pressure differential between the gallery and the spin chamber.

A fuel swirler with anti-rotation features is provided. A swirler assembly may comprise a swirler, a guide plate, and a retaining ring. The swirler, the guide plate, and/or the retaining ring may comprise recessions configured to receive a retaining element. The retaining element may be configured to interface with the recessions to create an interference in the swirler assembly. The interference may at least partially resist rotation of the guide plate with respect to the swirler.

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.

A swirler includes a swirler body and a plurality of axial swirl vanes extending radially outward from the swirler body. At least one of the swirler body or vanes includes a spring channel defined therethrough. A fuel injector for a gas turbine engine can include an inner air swirler and/or outer air swirler as described above.

A combustion system for a gas turbine engine includes a combustor dome. The combustor dome includes a fuel manifold with an inlet and nozzle components of a plurality of nozzles circumferentially spaced around the combustor dome. The fuel manifold and nozzle components are integrated with the combustor dome for fluid communication from the inlet to the nozzle components.