Patent ID: 6986255
Filing Date: 2006-01-17
Classification: F23D,F23R

Abstract:
1. A fuel injection system for a gas turbine, comprising: a pilot fuel injector; a pilot swirler that swirls air past the pilot fuel injector; a main airblast fuel injector having an aft end; inner and outer main swirlers that swirl air past the main airblast fuel injector; and an air splitter located between the pilot swirler and the inner main swirler, the air splitter comprising at least one aft end cone angled radially outboard and axially positioned close to or downstream of the main airblast fuel injector aft end, the air splitter dividing an outer pilot air stream exiting the pilot swirler from an inner main air stream exiting the inner main swirler to create a bifurcated recirculation zone.