GAS TURBINE COMPRISING A PLURALITY OF CAN-COMBUSTORS

Gas turbine for power plants, the gas turbine (1) comprising a compressor stage (2), a combustor stage (3) provided with a plurality of can-combustors (4), at least a turbine stage (5) and an outer casing (6) defining a plenum (20) and provided with plurality of portal holes (7) for supporting the c...

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Bibliographische Detailangaben
Hauptverfasser:	HUBER, Tobias Christoph, TAHENY, Oliver, ANGUISOLA MCFEAT, Jose, CORRADI, Mauro, UGEL, Diego, BHATNAGAR, Nishant
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBUSTION APPARATUS COMBUSTION ENGINES COMBUSTION PROCESSES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS ENGINE PLANTS IN GENERAL 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 MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES STEAM ENGINES WEAPONS
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Beschreibung
Zusammenfassung:	Gas turbine for power plants, the gas turbine (1) comprising a compressor stage (2), a combustor stage (3) provided with a plurality of can-combustors (4), at least a turbine stage (5) and an outer casing (6) defining a plenum (20) and provided with plurality of portal holes (7) for supporting the can-combustors (4); each portal hole (7) comprising an inner surface (13) facing and spaced from the relative can-combustor (4) in order to realize a gap (9) for allowing the compressed air to flow from the plenum (20) into the combustor can (4); wherein at each portal hole (7) the gas turbine (1) comprises a thermal managing device configured for applying at least a thermal treatment to the inner surface (13) of the relative portal hole (7).