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

PROBLEM TO BE SOLVED: To provide a fuel nozzle structure for an auxiliary air type vortex fuel nozzle in which steam injection is incorporated, assuring a high reliability and capable of reducing the power of an auxiliary unit. SOLUTION: The fuel nozzle 7 consists of a nozzle body 10 and a nozzle injection part 11 and is structured so that a liquid fuel 106, the auxiliary air 103, and the steam 107 are supplied to a nozzle injection part 11 through a liquid fuel passage 17, an auxiliary air passage 18, and a steam passage 19, respectively. The fuel nozzle 7 is embodied in a consolidated structure based on a cylindrical diametric structure consisting of a liquid fuel nozzle 30, an auxiliary air nozzle 37, a steam passage 44, and a combustion air ring-shaped passage 50 which are the constituent members of the nozzle injection part 11, in which the members are put in tight attachment in the radial direction and assembled, and at the time of steam injection, the operation is conducted in such a way that the supply of the auxiliary air is throttled. This makes the members slidable in the axial direction, which allows absorbing the thermal elongation difference between the members, and it is possible to reduce the power for the auxiliary air at the time of steam injection. COPYRIGHT: (C)2005,JPO&NCIPI