초록 ▼

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) i

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).

대표청구항 ▼

A gas turbine group, comprising: at least one compressor unit; a first combustion chamber for generating working gas, the first combustion chamber connected to receive compressed air from the compressor unit, the first combustion chamber being an annular combustion chamber having a plurality of prem

A gas turbine group, comprising: at least one compressor unit; a first combustion chamber for generating working gas, the first combustion chamber connected to receive compressed air from the compressor unit, the first combustion chamber being an annular combustion chamber having a plurality of premixing burners; a first turbine connected to received working gas from the first combustion chamber; a second turbine; a second combustion chamber connected to receive exhausted working gas from the first turbine and deliver working gas to the second turbine, the second combustion chamber comprising an annular duct forming a combustion space extending in a flow direction from an outlet of the first turbine to an inlet of the second turbine; means for introducing fuel into the second combustion chamber for self-ignition of the fuel; a plurality of vortex generating elements mounted in the second combustion chamber upstream of the means for introducing fuel; and, a single rotor shaft supported by not more than two bearings, the at least one compressor unit, first turbine and second turbine being connected on the rotor shaft.