FUEL NOZZLE FOR TURBINE COMBUSTOR HAVING DIFFUSION AND PREMIX COMBUSTION MODE, AND OPERATION METHOD FOR TURBINE COMBUSTOR

摘要

PURPOSE: To obtain a fuel nozzle functioning over the entire operating range of a turbine while reducing atmospheric pollutant in the exhaust gas extremely. ;CONSTITUTION: A fuel nozzle includes an annular chamber 23 defined between a housing 17 and a central tube 14. At the downstream end of the tube 14, inner and outer swirlers 18, 20 are provided in communication with an upstream chamber and a combustion zone downstream of the swirlers 18, 20. When fuel gas is supplied to the swirler 18, a portion of the air flowing through the chamber 23 is mixed with the supplied fuel for holding a diffusion flame in a downstream diffusion mixing cup. The balance of the air flowing through the chamber 23 through the swirler 20 is segregated from the air supplied to the swirler 18 by a circumferentially extending splitter vane 22. At an upstream portion of the chamber 23, a plurality of spokes 40 pass into the chamber 23 for supplying fuel gas to the chamber 23 when the nozzle operates in premix combustion mode. When operating in premix combustion mode, fuel gas is cut off from the swirler 18 and supplied to the spokes 40.;COPYRIGHT: (C)1996,JPO