Patent ID: 8573516
Filing Date: 2013-11-05
Classification: F02C,F05D,F23R

Abstract:
1. A fuel nozzle for a gas turbine engine, the nozzle comprising a monolithic stem member having an inlet end with at least one inlet for connection to a fuel supply, an outlet end with at least one outlet for connection to a spray tip assembly, and a central portion extending between the inlet and outlet ends, the stem member having at least one fuel conduit extending therethrough in connection with the inlet end and the outlet end, the stem member having a longitudinal axis and first and second transverse axes defined at least substantially perpendicularly to the longitudinal axis, a first outer dimension of the central portion defined parallel to the first transverse axis increasing from a first point located between the inlet and outlet ends to a second point adjacent the inlet end, a second outer dimension of the central portion defined parallel to the second transverse axis remaining at least substantially constant between the first and second points.