发明名称 |
GAS TURBINE SYSTEM, GAS TURBINE COMBUSTOR CONTROL DEVICE, AND GAS TURBINE COMBUSTOR CONTROL METHOD |
摘要 |
A gas turbine is provided with a combustor having a pilot nozzle, a first main nozzle, and a second main nozzle. A combustor control device has a load interruption detector which detects load interruption of the gas turbine, a pilot nozzle flow rate control unit which increases the amount of premixed fuel supplied to the pilot nozzle, based on the detection of the load interruption, a first main nozzle flow rate control unit which reduces the amount of premixed fuel supplied to the first main nozzles, based on the detection of the load interruption, and a second main nozzle flow rate control unit which reduces the amount of premixed fuel supplied to the second main nozzles to a predetermined amount, based on the detection of the load interruption, and then further reduces the amount of premixed fuel supplied after the elapse of a predetermined time. |
申请公布号 |
US2015354467(A1) |
申请公布日期 |
2015.12.10 |
申请号 |
US201414760519 |
申请日期 |
2014.02.18 |
申请人 |
Mitubishi Hitachi Power Systems, Ltd. |
发明人 |
KISHI Makoto;SONODA Takashi;UCHIDA Shinya;NAKAMURA Sosuke;MATSUMURA Yoshikazu;FUJII Satoko;YABE Tetsuya;HAGA Ryoichi |
分类号 |
F02C9/28;F02C7/22;F02C9/20 |
主分类号 |
F02C9/28 |
代理机构 |
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代理人 |
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主权项 |
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地址 |
Yokohama-shi, Kanagawa JP |