Patent ID: 6250066
Filing Date: 2001-06-26
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;a premix injector in fluid communication with said plenum and a source of fuel whereby the air and fuel are mixed, said premixer injector including an air blast fuel nozzle, a venturi, and a premix chamber, said venturi extending from an inlet to an exit in fluid communication with the combustion chamber, said venturi having a jet deflector along its interior wall near its exit; andan igniter for igniting said fuel and air mixture to initiate the formation of said hot gas.