Patent ID: 8607571

Claim:
An injector for a gas turbine engine comprising: a) a fuel feed arm configured and adapted to convey fuel from a main fuel circuit, a primary pilot fuel circuit, and a secondary pilot fuel circuit 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 air-blast atomizer defining an axis; c) a main fuel swirler inboard of the main prefilmer air-blast atomizer, the main fuel swirler and the main prefilmer air-blast atomizer 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 of the primary pilot fuel circuit; f) a secondary pilot fuel swirler component inboard of the air swirler and outboard of the primary pilot atomizer, the secondary pilot fuel swirler component including a prefilming air-blast 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; and h) a pilot air circuit inboard of the secondary pilot fuel swirler, wherein the primary pilot atomizer is inboard of the pilot air circuit.