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AssigneeROLLS-ROYCE plc
InventorsKarpaga Vipran KANNAN, Joseph R. HARDY, Ryan L. ROGERS, Andrés E. LEIVA GONZALEZ, Shahrokh SHAHPAR
Estimating the term…
A fuel swirl nozzle for a gas turbine engine comprises, in axial fuel flow sequence, a fuel inlet portion, a fuel stem portion, and a fuel/air swirler portion. An inlet to the fuel stem portion is fluidly sealed against the fuel inlet portion, and an outlet from the fuel stem portion is fluidly sealed against the fuel/air swirler portion. The fuel/air swirler portion has a cross-sectional profile that is generally dolioform shaped along an axis parallel to the engine's longitudinal axis, and has a first end and a second end. The first end of the fuel/air swirler portion has an air inlet face, and the second end of the fuel/air swirler portion has a fuel/air mixture outlet face. The first end comprises a rim portion enclosing the air inlet face in which the rim portion has a rim portion radius (rrim) normal to an outer circumference of the inlet face.
A fuel swirl nozzle for a gas turbine engine, the gas turbine engine having a longitudinal axis, the fuel swirl nozzle comprising, in axial fuel flow sequence, a fuel inlet portion, a fuel stem portion, and a fuel/air swirler portion, an inlet to the fuel stem portion being fluidly sealed against the fuel inlet portion, and an outlet from the fuel stem portion being fluidly sealed against the fuel/air swirler portion;
Dependencies are inferred from the claim text.