Patent ID: 8161751

Claim:
A fuel nozzle for a turbine engine, comprising: a generally cylindrical main body; a disc-shaped fuel swirler plate mounted inside the cylindrical main body adjacent an outlet end of the main body, wherein a plurality of fuel delivery apertures extend through the swirler plate, the fuel delivery apertures being angled with respect to the first and second flat surfaces of the swirler plate, and wherein a circular aperture is formed in the center of the disc-shaped fuel swirler plate; a pilot nozzle mounted inside the circular apreture; and a nozzle cap attached to the outlet end of the main body, wherein a diameter of the nozzle cap is gradually reduced from a first end which is coupled to the main body to second end which forms an outlet, and wherein an outlet side of the fuel swirler plate and an interior sidewall of the nozzle cap define a swirl chamber.