To alleviate restrictions on an operation period of a gas turbine while effectively using heat obtained by heat exchange with compressed air.
A gas turbine cooling system 50 includes: an air-cooling line 53 and a water-cooling line 54 through which compressed air extracted from an air compressor 11 of a gas turbine 10 flows and which introduces the compressed air into a high temperature section where the air is to be in contact with combustion gas in the gas turbine; air cooling device 55 which exchanges heat between the compressed air passing through the air-cooling line and the outside air to cool the compressed air and which returns the cooled compressed air into the air cooling line; a water-cooling device 58 which exchanges heat between the compressed air passing through the water-cooling line and water to cool the compressed air and which returns the cooled compressed air to the water-cooling line; and an air line switch 60 for selectively switching between an air-cooling condition to allow the compressed air to flow in the air-cooling line and a water-cooling condition to allow the compressed air to flow in the water-cooling line.
| WO/2000/037785 | HEAT ENGINE |
| JP2004332540 | VARIOUS OVERALL MOVING BLADE STEAM GAS TURBINE UNITED ENGINES |
| WO/2000/017504 | FUEL PREHEATING IN A GAS TURBINE |
Masatake Shiga
Tadashi Takahashi
Tetsuo Yamazaki
Yasushi Matsunuma
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