GAS TURBINE FUEL INJECTOR

摘要

A fuel injector (22) for a combustor and a gas turbine engine, comprises a nozzle tip assembly protruding through the combustor wall (28) into the chamber, the nozzle tip (26) including a first air passage (60) forming an annular array, a second air passage made up of an annular array of individual air passages (62) spaced radially from the first air passage (60), both communicating the pressurized air from outside the combustor wall (28) into the combustor. Fuel is injected through an annular fuel nozzle (54) between the first air passage (60) and the second air passages (62). Third air passages (64) are arranged in annular array in the injector tip (26) spaced radially outwardly from the second air passages (62) whereby the third passages (64) are arranged to shape the mixture of atomized fuel and air and to add supplemental air to the mixture.