PILOT NOZZLE IN GAS TURBINE COMBUSTOR

摘要

PROBLEM TO BE SOLVED: To offer flame stabilization benefits while minimizing NOx emissions generally associated with pilot nozzles.SOLUTION: A fuel nozzle for a gas turbine engine includes: an elongated centerbody; an elongated peripheral wall formed about the centerbody so as to define a primary flow annulus therebetween; a primary fuel supply and a primary air supply in the primary flow annulus; and a pilot nozzle. The pilot nozzle may be formed in the centerbody and include: axially elongated mixing tubes defined within a centerbody wall; a fuel port positioned on the mixing tubes for connecting each to a secondary fuel supply; and a secondary air supply configured so as to fluidly communicate with an inlet of each of the mixing tubes. Two or more of mixing tubes may be formed as canted mixing tubes that are configured for inducing a swirling downstream flow, while two or more of the mixing tubes may be axial inclined mixing tubes.SELECTED DRAWING: Figure 1