Gas turbine multi-stage combustion system

Details Gas turbine multi-stage combustion system Gas turbine multi-stage combustion system

1997-05-12

1998-09-08

Casaregola, Louis J.

Power plants

Combustion products used as motive fluid

Combustion products generator

60 39821, 60746, F23R 330, F23R 334

Patent

active

058028544

ABSTRACT:
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.

REFERENCES:
patent: 5069029 (1991-12-01), Kuroda et al.
patent: 5127229 (1992-07-01), Ishibashi et al.
patent: 5311742 (1994-05-01), Izumi et al.
patent: 5319935 (1994-06-01), Toon et al.

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