Patent ID: 7827795

Claim:
A fuel injector for use in a gas turbine engine having an engine case housed within a nacelle, the engine case including therein a compressor for compressing atmospheric air to form high pressure and high temperature compressed air that flows into a compressor discharge area upstream of and for use by a combustor also housed in the engine case, the nacelle forming a nacelle air bypass flow path around the engine case to allow low temperature nacelle air to flow therethrough, the fuel injector comprising: a central body defining a fuel flow passage extending between a fuel inlet and a fuel outlet; a cooling system including at least one orifice that defined a cooling air passage extending between an orifice cooling air inlet located in the compressor discharge area and a cooling air outlet located in the combustor; at least a portion of the cooling air passage extending through the engine case and into the nacelle air bypass flow path around the engine case, the cooling air passage thereafter extending through the central body and in thermal communication with the central body.