Gasturbine

Abstract

Abstract In a gas turbine assembly which essentially comprises 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 designed as annular combustion chamber. The said annular combustion chamber (3) is operated with a number of premixing burners (11), which are distributed on the circumference. The first turbine (4) is designed so that its exhaust gases have a temperature level which is higher than the spontaneous combustion temperature of the fuel (13) used in the second combustion chamber (5). The said second combustion chamber (5) comprises a burnerless, annular combustion space in which a number of vortex-generating elements (14) are incorporated. The turbo-machines, that is compressor (2), first turbine (4) and second turbine (6), are arranged on a rotor shaft (1), the said rotor shaft (1) being supported on two bearings (9, 15). <IMAGE>

Inventors

• 👤 Rolf Dr. Althaus
• 👤 Franz Farkas
• 👤 Peter Graf
• 👤 Fredy Hausermann
• 👤 Erhard Kreis

Bibliographic Details