DUAL FUEL GAS TURBINE COMBUSTOR

摘要

A combustor for a gas turbine having primary and secondary combustion zones. The combustor has a centrally disposed dual fuel nozzle that can supply a fuel rich mixture of either liquid and gaseous fuel to the primary combustion zone. The combustor also has primary gas fuel spray bars for supplying a lean mixture of gaseous fuel to the primary combustion zone via a first annular pre-mixing passage and secondary gas fuel spray bars for supplying a lean mixture of gaseous fuel to the secondary combustion zone via a second annular pre-mixing passage. In addition, the combustor also has a plurality of liquid fuel spray nozzles for introducing a lean mixture of liquid fuel into the secondary combustion zone via the second annular pre-mixing passage. The liquid fuel spray nozzles are disposed in fan shaped channels that are arranged in a circumferential array and that are connected to the second annular pre-mixing passage. The fan shaped channels cause expansion of the spray of fuel from the liquid spray nozzles and serve to ensure good atomization of the liquid fuel prior to its introduction into the second annular pre-mixing passage.