Patent ID: 6935116

Claim:
A gas turbine combustion system comprising: a casing having a first end, a second end, and a center axis, with said casing in fluid communication with compressed air from a compressor; an end cover fixed to said casing first end, said end cover having a first swirler having a plurality of passageways extending therethrough and at least one set of injectors in fluid communication with at least one fuel source, said passageways oriented generally perpendicular to said axis, and said one set of injectors located immediately adjacent to said first swirler for injecting fuel from said one fuel source at said first swirler; a dome located radially inward from said casing thereby forming a first passage between said casing and said dome, said dome having a first opening; a liner located radially inward from said casing, said liner having a first part located radially inward from at least a portion of said dome, thereby forming a second passage between said portion of said dome and said first part of said liner; an aft injector assembly located radially outward of said liner and radially inward of said casing, said aft injector assembly comprising: a manifold having at least one injection sector; another fuel source in fluid communication with said manifold; a plurality of third injectors located in said manifold to inject fuel into said second passage.