Gas turbine combustor and operating method thereof
View Patent ↗A gas turbine combustor has a combustion chamber into which fuel and air are supplied, wherein the fuel and the air are supplied into said combustion chamber as a plurality of coaxial jets.
1. A gas turbine combustor having a combustion chamber supplied with fuel and air, comprising:
a plurality of fuel nozzles each jetting the fuel;
a disc member arranged at a downstream side of said plurality of fuel nozzles with respect to fuel jet flows; and
a plurality of premixing flow passages made of holes formed in said disc member and having areas larger than areas of fuel jet holes of said plurality of fuel nozzles, respectively; and
wherein said plurality of fuel nozzles jet fuel through said plurality of premixing flow passages, respectively, from an upstream side to a downstream side of said combustion chamber.
2. A gas turbine combustor having a combustion chamber supplied with fuel and air, comprising:
a plurality of fuel nozzles each jetting the fuel;
a disc member arranged at a downstream side of said plurality of fuel nozzles with respect to fuel jet flows; and
a plurality of premixing flow passages made of holes formed in said disc member and having diameter areas larger than diameter areas of fuel jet holes of said plurality of fuel nozzles, respectively; and
wherein fuel from each of said plurality of fuel nozzles flows in said premixing flow passage along approximately a central portion thereof and the air from an outer peripheral side of said fuel nozzle flows in said premixing flow passage along the outer peripheral side thereof, and the fuel is jetted from an upstream side to a downstream side of said combustion chamber through said premixing flow passages.
3. A gas turbine combustor comprising:
a combustion chamber supplied with fuel and air;
a plurality of fuel nozzles each jetting the fuel;
a disc member arranged at a downstream side of said plurality of fuel nozzles with respect to fuel jet flows; and
a plurality of premixing flow passages made of holes formed in said disc member and having flow diameter areas larger than diameter areas of fuel jet holes of said plurality of fuel nozzles, respectively; and
wherein said plurality of fuel nozzles each jet fuel to approximately central portions of inlet portions of said premixing flow passages from an upstream side to a downstream side of said combustion chamber, respectively.
4. A method of operating a gas turbine combustor having a combustion chamber supplied with fuel and air, wherein
fuel is jetted from a plurality of fuel nozzles from an upstream side to a downstream side of the combustion chamber through a plurality of holes each being formed in a disc member and each hole having an area larger than a diameter area of a fuel jet hole of each of the plurality of fuel nozzles with the jetted fuel being mixed with air in the holes.