GAS TURBO-SET

GAS TURBO-SET

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) i...

Ausführliche Beschreibung

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Bibliographische Detailangaben
Hauptverfasser: HAUSERMANN FREDY, FARKAS FRANZ, GRAF PETER, ALTHAUS ROLF DR, KREIS ERHARD
Format: Patent
Sprache:eng
Schlagworte:
AIR INTAKES FOR JET-PROPULSION PLANTS
BLASTING
COMBUSTION APPARATUS
COMBUSTION ENGINES
COMBUSTION PROCESSES
CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
GAS-TURBINE PLANTS
GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGHVELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
HEATING
HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
LIGHTING
MECHANICAL ENGINEERING
WEAPONS
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Beschreibung
Zusammenfassung: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).