Patent ID: 8910480
Filing Date: 2014-12-16
Classification: F23D,F23R

Abstract:
1. A fuel injector for a combustor of a gas turbine engine, the fuel injector comprising: swirler means having an outer periphery and an inner periphery arranged coaxially about an axis and a plurality of vanes spaced circumferentially and extending between the inner and outer periphery, each vane has an axially forward leading edge and an axially rearward trailing edge, wherein adjacent vanes define an axially extending vane passage therebetween, the passage extending from the axially forward leading edge to the axially trailing edge, the vanes providing the vane passage with a pressure surface and an opposing suction surface, and wherein the vanes are radially inclined at an angle of between 5° and 20° to the true radius of the injector, and wherein the outer periphery extends axially into a prefilmer, wherein the prefilmer comprises at least one aperture constructed to supply a liquid fuel therethrough and provide a film of the liquid fuel on the prefilmer during use, and the prefilmer is constructed to have the film of liquid fuel contact the air stream exiting the swirler means during use.