GAS TURBINE COOLING SYSTEM, GAS TURBINE PLANT EQUIPPED WITH THE SAME AND METHOD OF COOLING HIGH-TEMPERATURE SECTION OF GAS TURBINE

A gas turbine cooling system includes an organic Rankine cycle in which a cycle medium repeatedly circulates through condensation and evaporation, an air-extraction line configured to extract compressed air from a compressor of a gas turbine, a cooling apparatus for cooling the compressed air while...

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Bibliographische Detailangaben
Hauptverfasser:	TOMITA Yasuoki, AKITA Eiji, AKAZAWA Shin, NAGAKAWA Takaaki, TAKASHIMA Yasuhiro, SAKAGAMI Naoki, ASAKUNO Jiro, TAKAMATSU Masaru
Format:	Patent
Sprache:	eng
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS ENGINE PLANTS IN GENERAL ENGINE PLANTS NOT OTHERWISE PROVIDED FOR ENGINES USING SPECIAL WORKING FLUIDS OR CYCLES GAS-TURBINE PLANTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING STEAM ACCUMULATORS STEAM ENGINE PLANTS STEAM ENGINES WEAPONS
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Beschreibung
Zusammenfassung:	A gas turbine cooling system includes an organic Rankine cycle in which a cycle medium repeatedly circulates through condensation and evaporation, an air-extraction line configured to extract compressed air from a compressor of a gas turbine, a cooling apparatus for cooling the compressed air while heating and evaporating the cycle medium condensed in the organic Rankine cycle using heat of the compressed air passing through the air-extraction line, and a cooling air line configured to guide the compressed air cooled by the cooling apparatus to a high temperature section of the gas turbine.