Gas turbine intake anti-icing device

A gas turbine intake anti-icing device for a gas turbine electric power generation system 1 is provided, the system having a gas turbine 2 and a power generator 20 that is coupled to the gas turbine and rotationally driven to generate electrical power. The device includes a power generator cooling m...

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Bibliographische Detailangaben
Hauptverfasser:	KIYOMASA YAHATA, FUSAO KUSUNOKI, SHUNSUKE NISHIE
Format:	Patent
Sprache:	eng
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS AIRCRAFT ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSIONTRANSMISSIONS IN AIRCRAFT AVIATION BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS COSMONAUTICS EQUIPMENT FOR FITTING IN OR TO AIRCRAFT FLYING SUITS GAS-TURBINE PLANTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MECHANICAL ENGINEERING PARACHUTES PERFORMING OPERATIONS TRANSPORTING WEAPONS
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Beschreibung
Zusammenfassung:	A gas turbine intake anti-icing device for a gas turbine electric power generation system 1 is provided, the system having a gas turbine 2 and a power generator 20 that is coupled to the gas turbine and rotationally driven to generate electrical power. The device includes a power generator cooling mechanism 21, 22, 23, 25 which takes in air from the outside and introduces the air into the power generator 20 to cool the power generator. An exhaust air supply path 31 connects a gas turbine air intake path 9 to an exhaust path 30 for air that is discharged from the power generator cooling mechanism after the power generator is cooled. The discharged air from the power generator cooling mechanism is supplied to the intake path of the gas turbine through the exhaust air supply path. The exhaust air supply path may be connected to the intake path nearest the inlet of the gas turbine engine.