HEAT EXCHANGERS AND COOLING METHODS FOR GAS TURBINES

A gas turbine (10) comprising a compressor (20), a combustor (30) downstream of the compressor, a turbine (40) downstream of the combustor, a heat exchanger (70), a first cooling fluid system (50) and a second cooling fluid system (60) is described. The first cooling fluid system and the second cool...

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Bibliographische Detailangaben
Hauptverfasser:	Simon-Delgado, Carlos, Taheny, Oliver Joseph, Alberti, Luca, Jemora, Daniel, Olmes, Sven
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS ENGINE PLANTS IN GENERAL GAS-TURBINE PLANTS 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:	A gas turbine (10) comprising a compressor (20), a combustor (30) downstream of the compressor, a turbine (40) downstream of the combustor, a heat exchanger (70), a first cooling fluid system (50) and a second cooling fluid system (60) is described. The first cooling fluid system and the second cooling fluid system are each configured and arranged to extract a cooling fluid from the compressor and to cool a part of the gas turbine using the cooling fluid. The first cooling fluid system and the second cooling fluid system each extend from the compressor to the heat exchanger and from the heat exchanger to the part of the gas turbine to be cooled. The heat exchanger is configured and arranged to exchange heat from the cooling fluid in the second cooling fluid system to the cooling fluid in the first cooling fluid system. A rotor cover (100) with a heat exchanger and methods of operation are also described.