Abstract: A dual fuel injector for injecting liquid and/or gaseous fuel into a gas turbine engine includes a plurality of hollow spoke members for injecting gaseous fuel that are located upstream of a plurality of main air swirling vanes that are in turn upstream of a plurality of air-blast atomizers for injecting main liquid fuel. A pilot fueling arrangement is provided that is capable of starting the gas turbine engine using either gaseous or liquid fuel. The injector includes a labyrinth-shaped cooling passage capable of providing cooling air to cylindrical walls of an injector centerbody.

Abstract: The present method of making a workpiece having a plurality of holes defined therein includes the plurality of holes defining a specific flow at a specific flow condition.

Abstract: Past fuel injection nozzles have attempted to provide a structure to reduce tip temperatures. Such nozzles have failed to attain adequate reduction of tip temperatures without increasing the quantity of cooling air required. The present fuel injector structure has resulted in reduced tip temperatures without increasing the quantity of cooling air required. The structure includes a shell having an inner member positioned therein forming a first chamber therebetween, an end piece forming a second chamber between the inner member and the end piece. An inner body has a plurality of first angled passages formed therein and communicates between the second chamber and a passage. A flow of combustor air through the second chamber contacts an air side of the end piece resulting in a combustor side being cooled. The unique structure of the fuel injector nozzle provides improved tip cooling without increasing the quality of cooling air and improves the efficiency of the gas turbine engine.