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AssigneeABB Management AG
InventorsRolf Althaus, Franz Farkas, Peter Graf, Fredy Hausermann, Erhard Kreis
Estimating the term…
In a gas turbine group which consists essentially of a compressor (2), a first combustion chamber (3), a first turbine (4), a second combustion chamber (5) and a second turbine (6), the first combustion chamber (3) is configured as an annular combustion chamber. This annular combustion chamber (3) is operated by a number of premixing burners (11) which are distributed at the periphery. The first turbine (4) is designed in such a way that its exhaust gases have a temperature level which is above the self-ignition temperature of the fuel (13) used in the second combustion chamber (5). This second combustion chamber (5) consists of a burnerless, annular combustion space in which a number of vortex-generating elements (14) are integrated. The turbomachines, namely compressor (2), first turbine (4) and second turbine (6) are disposed on a rotor shaft (1), this rotor shaft (1) being supported in two bearings (9, 15).
A method for operating a gas turbine group having at least one compressor, a first annular combustion chamber downstream of the compressor, a first turbine downstream of the first combustion chamber, a second combustion chamber downstream of the first turbine, and a second turbine downstream of the second combustion chamber, the second combustion chamber extending from an outlet plane of the first turbine to an inlet plane of the second turbine, the second combustion chamber being operable without ignition apparatus, the method comprising the steps of:
Dependencies are inferred from the claim text.