Gas turbine combustor and operating method thereof
AssigneeHitachi, Ltd.
InventorsHiroshi Inoue, Tomomi Koganezawa, Nariyoshi Kobayashi, Isao Takehara
Life of this patent
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Abstract
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.
Claims11
A gas turbine combustor having 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.
A gas turbine combustor comprising a fuel nozzle for injecting fuel into a combustion chamber and an air hole for injecting air into said combustion chamber, wherein the fuel nozzle and the air hole are disposed so that the fuel and the air are injected into said combustion chamber as a plurality of coaxial jets.
A gas turbine combustor comprising a fuel nozzle, an air hole and a combustion chamber, wherein fuel and air are injected into said combustion chamber as a large number of small diameter coaxial jets.
A method of operating a gas turbine combustor having 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.
A method of operating a gas turbine combustor having a combustion chamber into which fuel and air are supplied, wherein a plurality of fuel nozzles for injecting the fuel are provided, the fuel nozzles being partitioned into a plurality of fuel supply systems, the flow rate of each fuel being individually controlled according to the load on the gas turbine, and the fuel and the air being supplied as a plurality of coaxial jets.
Dependencies are inferred from the claim text.