초록 ▼

In a gas turbine combustor of the present invention, a pilot fuel nozzle is composed of at least two systems with different hole diameters, and the fuel flow rate of each system can be controlled independently. Also, even if the operation of main burners is switched in accordance with high or low lo

In a gas turbine combustor of the present invention, a pilot fuel nozzle is composed of at least two systems with different hole diameters, and the fuel flow rate of each system can be controlled independently. Also, even if the operation of main burners is switched in accordance with high or low load, the pilot fuel is selected accordingly. Further, the pilot fuel differential pressure is kept high to effect stable supply of fuel, and stable combustion is maintained.

대표청구항 ▼

[ We claim:] [1.] A gas turbine combustor comprising a plurality of main burners spaced apart about a circumference and arranged around a pilot fuel nozzle, said main burners being divided into at least first and second groups which are operable independently of each other and which occupy different

[ We claim:] [1.] A gas turbine combustor comprising a plurality of main burners spaced apart about a circumference and arranged around a pilot fuel nozzle, said main burners being divided into at least first and second groups which are operable independently of each other and which occupy different portions of said circumference, said pilot fuel nozzle including first and second systems of pilot holes which are operable independently of each other, said first system comprising a plurality of pilot holes of a first diameter and said second system comprising a plurality of pilot holes of a second diameter smaller than said first diameter, the pilot holes of said second system being located radially inward of the first system of pilot holes.