GAS TURBINE SYSTEM, GAS TURBINE COMBUSTOR CONTROL DEVICE, AND GAS TURBINE COMBUSTOR CONTROL METHOD

WIPO Patent Application WO/2014/129458

A1

A gas turbine system equipped with a gas turbine (10) and a combustor control device (11). The gas turbine (10) is equipped with a combustor (12) having a pilot nozzle (13), first main nozzles (14), and second main nozzles (15). The combustor control device (11) has: a load interruption detection device (16) that detects interruptions in the load of the gas turbine (10); a pilot nozzle flow volume control unit (17) that, on the basis of the detection of a load interruption, increases the amount of a premixed fuel supplied to the pilot nozzle (13); a first main nozzle flow volume control unit (18) that, on the basis of the detection of a load interruption, reduces the amount of the premixed fuel supplied to the first main nozzles (14); and a second main nozzle flow volume control unit (19) that, on the basis of the detection of a load interruption, reduces the amount of the premixed fuel supplied to the second main nozzles (15) to a prescribed amount, and then further reduces the amount of fuel supplied after a prescribed amount of time has elapsed.

KISHI MAKOTO (JP)
SONODA TAKASHI (JP)
UCHIDA SHINYA (JP)
NAKAMURA SOSUKE (JP)
MATSUMURA YOSHIKAZU (JP)
FUJII SATOKO (JP)
YABE TETSUYA (JP)
HAGA RYOICHI (JP)

PCT/JP2014/053754

August 28, 2014

February 18, 2014

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MITSUBISHI HITACHI POWER SYS (JP)

F02C9/34; F02C7/00; F02C7/228; F02C7/232; F02C9/00; F02C9/28; F23R3/28

JPH08178290A	1996-07-12
JPH05149544A	1993-06-15
JP2011085105A	2011-04-28

MORI Ryuichirou et al. (JP)
Woods Ryuichiro (JP)

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