Importance

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Abstract

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. The fuel inlet portion is configured to receive a flow of a fuel, with 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. The fuel/air swirler portion comprises an outer air swirler and an inner air swirler, with the inner air swirler being positioned concentrically within the outer air swirler. The outer air swirler comprises a plurality of first vanes that are arranged in an annular array within an outer air swirler body and is configured to impose a first rotational flow component on an air flow entering the outer air swirler. The inner air swirler has a plurality of second vanes that are arranged in an annular array within an inner air swirler body and are configured to impose a second rotational flow component on an air flow entering the inner air swirler. The fuel stem portion passes radially inwardly through the outer air swirler to a region radially between the outer air swirler and the inner air swirler. The inner air swirler also comprises an annular fuel gallery that is formed on a radially outwardly facing surface such that the flow of fuel enters the fuel gallery before being atomised into the air flow passing through the inner air swirler, and then further atomised into the air flow passing through the outer air swirler.

First Claim