NOZZLE WITH MULTI-TUBE FUEL SUPPLY PASSAGEWAY FOR GAS TURBINE ENGINES

摘要

A pilot fuel nozzle (10) for a gas turbine combustor includes an igniter (20) forming a central body (19) extending along a longitudinal center of the nozzle (10). A nozzle tip (18) includes a plurality of circumferentially spaced fuel passages (32) and a plurality of circumferentially spaced air passages (54) extending to an outer side of the nozzle tip (18). The central body (19) extends through a center of the nozzle tip (18) for producing a spark to ignite a fuel/ air mixture adjacent to the nozzle tip (18). A plurality of eventually spiral fuel tubes (32) extend along the central body (19), each of the fuel tubes (32) having an outlet end (38) engaged on the nozzle tip (18) for delivery of fuel from the nozzle tip (18) into a combustion chamber. An outer sleeve (16) surrounds the fuel tubes (32) and defines an annular space (52) in fluid communication with the air passages (54) of the nozzle tip (18) between the outer sleeve (16) and the central body (19). The outer sleeve (16) may further include an annular diffusion passage (72), and an annular premix passage (74) for additional or alternative fuel supply.