Gas turbine fuel injector

摘要

A fuel injector for a combustor and a gas turbine engine, wherein the combustor includes a combustor wall defining a combustion chamber tube surrounded by pressurized air. The injector comprises a nozzle tip assembly protruding through the combustor wall into the chamber, the nozzle tip including a first air passage forming an annular array of individual air passages spaced radially from the first air passage and communicating the pressurized air from outside the combustor wall into the combustor. A fuel gallery extends through the fuel injector tip and defines an annular fuel nozzle radially within the first air passages, whereby the first air passages are arranged to atomize the fuel emanating from the annular fuel nozzle, and second fuel passages are arranged in annular array in the injector tip spaced radially outwardly from the first air passages whereby the second passages are arranged to shape the mixture of atomized fuel and air and to add supplemental air to the mixture.