Patent ID: 7237730

Claim:
A fuel nozzle for a gas turbine engine, the nozzle comprising: a body defining at least a central fuel passage therethrough, the fuel passage having an axis defining an axial direction and exiting the body through a spray orifice coaxial with the axis, the body having a conical peripheral surface with the spray orifice disposed at an apex of the conical peripheral surface, the conical peripheral surface including a plurality of channels defined therein, the channels radiating along the conical peripheral surface around the spray orifice, each of the channels having a cross-sectional contour that does not exhibit any undercut portion when viewed along any axis parallel to the axis, thereby permitting withdrawal of a channel forming tool form the channels in a direction parallel to the axis; and an annular collar mounted to the body, the collar and the conical surface of the body co-operating to define a plurality of enclosed air swirl passages corresponding to the channels.