초록 ▼

A fuel injector for a gas turbine engine includes a nozzle body defining a central axis and having a main fuel circuit. An air circuit is formed within the nozzle body inboard of the main fuel circuit. A primary pilot fuel circuit is formed within the nozzle body inboard of the air circuit. A second

A fuel injector for a gas turbine engine includes a nozzle body defining a central axis and having a main fuel circuit. An air circuit is formed within the nozzle body inboard of the main fuel circuit. A primary pilot fuel circuit is formed within the nozzle body inboard of the air circuit. A secondary pilot fuel circuit is formed within the nozzle body inboard of the air circuit and outboard of the primary pilot fuel circuit.

대표청구항 ▼

1. A fuel injector for a gas turbine engine comprising: a) a nozzle body defining a central axis and having three fuel circuits comprising a main fuel circuit having a main fuel inlet, a primary pilot fuel circuit having a primary pilot fuel inlet and a secondary pilot fuel circuit having a secondar

1. A fuel injector for a gas turbine engine comprising: a) a nozzle body defining a central axis and having three fuel circuits comprising a main fuel circuit having a main fuel inlet, a primary pilot fuel circuit having a primary pilot fuel inlet and a secondary pilot fuel circuit having a secondary pilot fuel inlet, wherein the main fuel circuit includes a pre-filming air-blast atomizer;b) an air circuit formed within the nozzle body inboard of the main fuel circuit;c) a primary pilot fuel circuit formed within the nozzle body inboard of the air circuit;d) a secondary pilot fuel circuit formed within the nozzle body inboard of the air circuit and outboard of the primary pilot fuel circuit, wherein the primary pilot fuel circuit is configured and adapted to have a lower flow number than the secondary pilot fuel circuit; ande) a pilot air circuit inboard of the secondary pilot fuel circuit, wherein the primary pilot fuel circuit is inboard of the pilot air circuit. 2. An injector as recited in claim 1, wherein at least one of the main fuel circuit and secondary pilot fuel circuit includes a diverging prefilming air-blast atomizer. 3. An injector as recited in claim 1, wherein the primary pilot fuel circuit includes a pressure swirl atomizer. 4. An injector as recited in claim 3, wherein the pressure swirl atomizer is defined in an inner air swirler along the axis of the nozzle body. 5. An injector as recited in claim 1, wherein the primary pilot fuel circuit includes a primary pressure swirl atomizer on the axis of the nozzle body. 6. An injector as recited in claim 1, wherein each of the primary and secondary pilot fuel circuits includes a separate atomizer orifice. 7. An injector as recited in claim 1, further comprising an outer air circuit formed in the nozzle body outboard of the main fuel circuit. 8. An injector for a gas turbine engine comprising: a) a fuel feed arm configured and adapted to convey fuel from three fuel circuits comprising a main fuel circuit having a main fuel inlet, a primary pilot fuel circuit having a primary pilot fuel inlet, and a secondary pilot fuel circuit having a secondary pilot fuel inlet, for combustion in a combustor of a gas turbine engine;b) a nozzle body depending from the fuel feed arm and including a main prefilmer defining an axis;c) a main fuel swirler inboard of the main prefilmer, the main fuel swirler and prefilmer defining a portion of the main fuel circuit therebetween;d) at least one air swirler inboard of the main fuel swirler, the main fuel swirler and the at least one air swirler defining at least one air circuit therebetween;e) a primary pilot atomizer inboard of the at least one air swirler, wherein the primary pilot atomizer forms a portion the primary pilot fuel circuit;f) a secondary pilot fuel swirler component inboard of the air swirler and outboard of the primary pilot atomizer;g) a secondary pilot fuel swirler inboard of the secondary pilot fuel swirler component and outboard of the primary pilot atomizer, the secondary pilot fuel swirler component and secondary pilot fuel swirler forming a portion of the secondary pilot fuel circuit therebetween, wherein the primary pilot fuel circuit is configured and adapted to have a lower flow number than the secondary pilot fuel circuit; andh) a pilot air circuit inboard of the secondary pilot fuel swirler, wherein the primary pilot atomizer is inboard of the pilot air circuit. 9. An injector as recited in claim 8, wherein the secondary pilot fuel circuit includes a prefilming air-blast atomizer. 10. An injector for a gas turbine engine comprising: a) a fuel feed arm configured and adapted to convey fuel for combustion in a combustor of a gas turbine engine from three fuel circuits comprising a main fuel circuit having a main fuel inlet, a primary pilot fuel circuit having a primary pilot fuel inlet, and a secondary pilot fuel circuit having a secondary pilot fuel inlet;b) a nozzle body depending from the fuel feed arm and including an annular main fuel atomizer defining an axis, the annular main fuel atomizer being an air-blast pre-filming atomizer and defining a portion of the main fuel circuit;c) a primary pilot fuel atomizer inboard of the annular main fuel atomizer, the primary pilot fuel atomizer being pressure swirl atomizer and defining a portion of the primary pilot fuel circuit;d) a secondary pilot fuel atomizer inboard of the annular main fuel atomizer and outboard of the primary pilot fuel atomizer, the secondary pilot fuel atomizer being an airblast prefilming atomizer and defining a portion of the secondary pilot fuel circuit, wherein the primary pilot fuel circuit is configured and adapted to have a lower flow number than the secondary pilot fuel circuit; ande) an air circuit formed within the nozzle body inboard of the secondary pilot fuel atomizer and outboard of the primary fuel atomizer. 11. An injector as recited in claim 10, wherein the main fuel circuit includes a pre-filming air-blast atomizer.