To provide a gas turbine having improved efficiency and allowing the longer life of stationary blades by cooling the stationary blades depending on peripheral temperature distribution in a gas turbine flow path.
In the gas turbine, high-pressure air discharged from an air compressor 1 is supplied to a combustor 22 and high-temperature and high-pressure combustion gas is generated by combustion with a fuel separately supplied into the combustor 22 to drive the turbine 2. As cooling means for cooling blades 4A, 4B of preset stage stationary blades 4 arranged in the turbine depending on the peripheral temperature distribution in the turbine flow path, cooling holes 30 in the blade 4A opposed to the outlet of the combustor 22, from which a cooling medium supplied into the blade is blown, are provided more than cooling holes 30 in the other blade 4B.
UCHIDA SUMIO
ISHIZAKA KOICHI
MATSUMOTO KAZUYUKI
| JP2001289003A | 2001-10-19 | |||
| JP2001107703A | 2001-04-17 |
Tadahiro Mitsuishi
Yasuyuki Tanaka
Hiroshi Matsumoto