Patent ID: 8763401

Claim:
An integrated fuel nozzle and ignition assembly for a gas turbine engine comprising: a nozzle head having a body adapted to extend through a corresponding hole defined in a combustor of the gas turbine engine and comprising a fuel nozzle portion and an igniter portion, the fuel nozzle portion defining a fuel passage extending therethrough between a fuel inlet and a fuel outlet for directing a fuel flow into a combustion chamber of the combustor, wherein fuel is discharged from the fuel outlet as a fuel cone extending along a fuel axis, wherein the fuel axis extends along the fuel inlet an fuel outlet of the fuel nozzle portion and into the combustor, the igniter portion projecting laterally from the fuel nozzle portion on a side thereof and comprising an igniter receiving cavity positioned adjacently and laterally on a side of the fuel passage; and an igniter mounted in the igniter receiving cavity outwardly from the fuel cone for igniting the fuel flow discharged by the fuel passage, wherein the igniter comprises an igniter plug for generating sparks propagating along a spark axis, and wherein the spark axis and the fuel axis intersect together forwardly from the nozzle head at a predetermined angle α for igniting the combustible mixture at an external surface of the fuel cone.