초록 ▼

A gas turbine combustor includes a side wall, for defining a combustion volume, having upstream and downstream ends, a pilot nozzle, disposed adjacent the upstream end of the side wall, for discharging a pilot fuel to form a diffusion flame in the combustion volume, and a plurality of main nozzles,

A gas turbine combustor includes a side wall, for defining a combustion volume, having upstream and downstream ends, a pilot nozzle, disposed adjacent the upstream end of the side wall, for discharging a pilot fuel to form a diffusion flame in the combustion volume, and a plurality of main nozzles, provided around the pilot nozzles, for discharging a fuel-air mixture to form premixed flames in the combustion volume. Film air is supplied into the combustion volume downstream of the main nozzles along the inner surface of the side wall to reduce the fuel-air ratio in a region adjacent the inner surface of the side wall and to restrain a combustion-driven oscillation in the combustion volume.

대표청구항 ▼

1. A gas turbine comprising:a side wall having a plurality of oscillation damping orifices there through and upstream and downstream ends, the side wall defining a combustion volume; a pilot nozzle disposed adjacent the upstream end of the side wall and configured to discharge a pilot fuel to form a

1. A gas turbine comprising:a side wall having a plurality of oscillation damping orifices there through and upstream and downstream ends, the side wall defining a combustion volume; a pilot nozzle disposed adjacent the upstream end of the side wall and configured to discharge a pilot fuel to form a diffusion flame in the combustion volume; a plurality of main nozzles provided around the pilot nozzle and configured to discharge a fuel-air mixture to form premixed flames in the combustion volume; and an acoustic liner attached to an outer surface of the side wall in a region where the oscillation damping orifices are located, the acoustic liner comprising a plurality of circumferentially distinct liner segments attached to the outer surface of the side wall, wherein the plurality of oscillation damping orifices are located in a region directly adjacent and downstream of the main nozzles. 2. A gas turbine combustor according to claim 1, wherein the liner segments include bellows portions for reducing a thermal stress due to a temperature difference between the side wall of the gas turbine combustor and the respective liner segments.3. A gas turbine combustor according to claim 2, further comprising:catches attached to the outer surface of the side wall; and engagement portions in the liner segments for engaging the catches, wherein the engagement of the engaging portions with the catches allows the liner segments to be attached to the outer surface of the side wall. 4. A gas turbine combustor according to claim 3, further comprising:sealing members provided between the engaging portions and the catches or the side wall. 5. A gas turbine combustor according to claim 1, wherein the side wall includes a plurality of steam passages for allowing cooling steam to flow therethrough and the oscillation damping orifices are disposed in lines between the steam passages.6. A gas turbine combustor according to claim 5, wherein the acoustic liner includes a peripheral wall facing the side wall of the combustor and a plurality of air cooling orifices defined in the peripheral wall disposed in lines aligned over the lines of the oscillation damping orifices.7. A gas turbine combustor according to claim 6, wherein the air cooling orifices are disposed to face wall portions between adjoining oscillation damping orifices.