Patent ID: 7677471
Filing Date: 2010-03-16
Classification: F23D,F23R,Y10T

Abstract:
1. A fuel nozzle for a gas turbine engine, the fuel 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 open-section channels defined therein, the channels being distributed along the conical peripheral surface around the spray orifice, each channel having an open section defined by a bottom wall and opposed sidewalls, the angle θ between each of the sidewalls and the bottom wall being equal to or greater than the angle δ between the bottom wall and the axial direction, thereby allowing withdrawal of a channel forming tool from the channel in a direction parallel to the axis; an annular collar mounted to the body, the collar and conical surface of the body co-operating to define a plurality of enclosed air swirl passages corresponding to the channels.