Patent ID: 6070406
Filing Date: 2000-06-06
Classification: F02C,F16K,F23L,F23R

Abstract:
A gas turbine engine comprising:a compressor providing pressurized air;a turbine for expanding a hot gas;a combustor disposed between said compressor and said turbine; said combustor comprising:a combustion chamber defined by a combustor wall;a plenum circumscribing said combustor wall and receiving said pressurized air from said compressor;an injector for injecting a fuel and air mixture into said combustion chamber;an igniter for igniting said fuel and air mixture to initiate the formation of said hot gas;a dilution zone just upstream of said turbine, said dilution zone receiving a portion of the air in said plenum through at least one dilution hole; anda bypass system for controlling the flow of the remaining portion of said air in said plenum to said injector and said dilution zone, said remaining portion of said air flowing to said dilution zone bypassing said dilution hole.