Patent ID: 6996991
Filing Date: 2006-02-14
Classification: F23D,F23R

Abstract:
1. A fuel system for a turbine engine, comprising: a first premix injector assembly comprising at least four injectors, wherein at least first and second injectors of the at least four injectors of the first premix injector assembly are positioned adjacent each other in the turbine engine and at least third and fourth injectors of the at least four injectors of the first premix injector assembly are positioned adjacent each other in the turbine engine; a second premix injector assembly comprising at least four injectors, wherein at least first and second injectors of the at least four injectors of the second premix injector assembly are positioned adjacent each other in the turbine engine and at least third and fourth injectors of the at least four injectors of the second premix injector assembly are positioned adjacent each other in the turbine engine; a plurality of fuel injectors positioned radially outward from the first and second premix fuel injector assemblies; at least one pilot nozzle, wherein the at least four injectors of the first premix injector assembly and the at least four injectors of the second premix injector assembly form a ring around the pilot nozzle; wherein the first and second injectors forming a portion of the first premix injector assembly are positioned between the first and fourth injectors forming a portion of the second premix injector assembly and the third and fourth injectors forming a portion of the first premix injector assembly are positioned between the second and third injectors forming a portion of the second premix injector assembly; and wherein the fuel system is capable of emitting fuel into the turbine engine through the first premix injector assembly without simultaneously emitting fuel into the turbine engine through the second premix injector assembly.