Patent ID: 8752386

Claim:
A fuel injector for use in a combustor assembly of a gas turbine engine, the fuel injector comprising: a main body having an inlet end and an outlet end and defining a longitudinal axis defining a longitudinal direction of the fuel injector and extending between said outlet end and said inlet end, said main body comprising a plurality of air/fuel passages extending therethrough, each air/fuel passage including an inlet that receives air from a source of air and an outlet, wherein said air/fuel passages comprise hexagonal-shaped passages positioned in a honeycomb configuration; and a fuel supply structure extending in said longitudinal direction and communicating with and supplying fuel to said air/fuel passages for providing an air/fuel mixture within each air/fuel passage, the air/fuel mixtures exiting said main body through respective air/fuel passage outlets, wherein said fuel supply structure includes isolated fuel distribution passages that individually deliver respective portions of fuel from said fuel supply structure to each of said air/fuel passages.