초록 ▼

A gas turbine combustion system includes a cylindrical combustor, a plurality of combustion sections in an arrangement spaced apart in an axial direction of the combustor, a plurality of fuel supply lines independently connected to the combustion sections, respectively, premixed fuel supply sections

A gas turbine combustion system includes a cylindrical combustor, a plurality of combustion sections in an arrangement spaced apart in an axial direction of the combustor, a plurality of fuel supply lines independently connected to the combustion sections, respectively, premixed fuel supply sections respectively provided for the fuel supply lines for supplying a premixed fuel, a diffusion combustion fuel supply section for supplying a diffusion combustion fuel to the combustion sections, and a control switching over the fuel supply sections to selectively supply either one of the premixed fuel and the diffusion combustion fuel. The premixed fuel at a first combustion stage is burned while the premixed fuel of subsequent stage is ignited by a high-temperature gas generated from combustion of the premixed fuel of a preceding combustion stage.

대표청구항 ▼

[ What is claimed is:] [1.] A gas turbine combustion system comprising:a cylindrical combustor having one end closed by a header;a plurality of combustion sections in an arrangement spaced apart in an axial direction of the combustor;a plurality of fuel supply lines independently connected to said c

[ What is claimed is:] [1.] A gas turbine combustion system comprising:a cylindrical combustor having one end closed by a header;a plurality of combustion sections in an arrangement spaced apart in an axial direction of the combustor;a plurality of fuel supply lines independently connected to said combustion sections, respectively;a plurality of igniter means respectively provided for said combustion sections and initiating the combustion in the respective combustion sections;a plurality of premixed fuel supply sections respectively provided for said fuel supply lines and supplying a premixed fuel and having a premixed fuel nozzle;a diffusion combustion fuel supply section supplying a diffusion combustion fuel to one of the combustion sections and having a diffusion combustion fuel nozzle; anda control unit switching over said fuel supply sections and selectively supplying either one of the premixed fuel and the diffusion combustion fuel;said combustion sections including a first combustion stage, a second combustion stage and at least three succeeding combustion stages, totally at least five combustion stages, and said fuel supply lines including a fuel supply line for the first combustion stage which is divided into two fuel supply sections, one of which is connected to the diffusion combustion fuel nozzle of the diffusion fuel supply section and another one of which is connected to the premixed fuel nozzle of the premixed fuel supply section so that the control unit switches over a combustion condition from diffusion combustion to premixed combustion during operation of the gas turbine combustion system, and in at least one of said combustion stages, the premixed fuel is burned by the igniter means.