GAS TURBINE COMBUSTOR, FUEL INJECTION NOZZLE AND FUEL INJECTION METHOD OF GAS TURBINE COMBUSTOR

摘要

PROBLEM TO BE SOLVED: To attain combustion stability up to the middle of speed-up from ignition; and to reduce delivery pressure of a fuel supply pump without arranging large-scale equipment such as a large capacity compressor and a heat exchanger applied to an air assist type liquid fuel injection nozzle in a dual orifice type liquid fuel injection nozzle for a gas turbine combustor. SOLUTION: Air is introduced up to the middle of speed-up from ignition by connecting a pipe for introducing the air to the downstream side of a pressurizing valve arranged on the upstream side of a main nozzle. Combustion air is turned by arranging a turning unit outside the fuel injection nozzle, and the combustion air is turned by contacting with the combustion chamber side tip of the fuel injection nozzle. COPYRIGHT: (C)2004,JPO&NCIPI