Patent ID: 8429914

Claim:
A fuel injection system for a gas turbine, comprising: a mains airblast fuel injector having an annular shape; an inner mains swirler for swirling air past said mains airblast fuel injector, said inner mains swirler being concentric with said mains airblast fuel injector and being located radially inward of said mains airblast injector; and an outer mains swirler for swirling air past said mains airblast fuel injector, said outer mains swirler being concentric with said mains airblast fuel injector and being located radially outward of said mains airblast injector, and said outer mains swirler being bounded at its outermost radial extent by an annular outer wall, which is concentric with said mains airblast fuel injector, a portion of said outer wall extending beyond said outer mains swirler to lie downstream of said mains airblast fuel injector; wherein the portion of said outer wall lying downstream of said mains airblast fuel injector tapers radially inwardly in the downstream direction; and said fuel injection system is mounted in an upstream wall of a combustion chamber, said tapered portion of said outer wall extending to said upstream wall.