Patent ID: 6895755

Claim:
A fuel injector for a gas turbine engine, the fuel injector comprising: a housing stem having a fuel conduit for carrying fuel; a nozzle supported by the housing stem, said nozzle including a fuel passageway directing fuel from the fuel conduit downstream to a discharge orifice at a discharge end of the nozzle, the fuel passageway defined in part by a primary adapter and having an outer surface with a distinct annular, radially-outwardly-projecting shoulder at an upstream end of the primary adapter, the shoulder having a continuously annular, upstream-facing surface, extending radially outward to a rounded peripheral annular edge with a radius, the edge defining a continuously annular passage portion with an internal wall of an outer fuel conduit portion, the adapter inwardly tapering smoothly downstream of the shoulder to a downstream cylindrical portion, to restrict flow through the passageway and provide substantially uniform distribution of flow through the passageway downstream of the shoulder.