GAS TURBINE SYSTEM, GAS TURBINE COMBUSTOR CONTROL DEVICE, AND GAS TURBINE COMBUSTOR CONTROL METHOD
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.
1 - 7 . (canceled)
8 . A gas turbine combustor control device comprising:
a load interruption detector which detects load interruption of a gas turbine;
a pilot nozzle flow rate control unit which increases the amount of premixed fuel supplied to a pilot nozzle, based on detection of the load interruption;
a first main nozzle flow rate control unit which reduces the amount of premixed fuel supplied to a first main nozzle, based on detection of the load interruption; and
a second main nozzle flow rate control unit which reduces the amount of premixed fuel supplied to a second main nozzle to a predetermined amount, based on detection of the load interruption, and then further reduces the amount of premixed fuel supplied after the elapse of a predetermined time.
9 . The gas turbine combustor control device according to claim 8 , wherein the combustor control device temporarily reduces a flow rate of the first main nozzle, based on detection of the load interruption.
10 . The gas turbine combustor control device according to claim 8 , wherein the combustor control device reduces the amount of premixed fuel supplied to the second main nozzle with a parameter required for a flame as an indicator.
11 . The gas turbine combustor control device according to claim 8 , wherein the combustor control device sets delay time when reducing the amount of premixed fuel supplied to the second main nozzle to a predetermined amount, based on detection of the load interruption, and then further reducing the amount of premixed fuel supplied after the elapse of a predetermined time.
12 . The gas turbine combustor control device according to claim 8 , wherein the combustor control device includes adjustment of an opening degree of an inlet guide vane provided in the gas turbine.
13 . A gas turbine system comprising:
a gas turbine provided with a combustor comprising
a pilot nozzle which injects premixed fuel, and
a first main nozzle and a second main nozzle which are provided around the pilot nozzle and inject premixed fuel; and
a combustor control device according to claim 8 .
14 . A gas turbine system comprising:
a gas turbine provided with a combustor comprising
a pilot nozzle which injects premixed fuel, and
a first main nozzle and a second main nozzle which are provided around the pilot nozzle and inject premixed fuel; and
a combustor control device according to claim 9 .
15 . A gas turbine system comprising:
a gas turbine provided with a combustor comprising
a pilot nozzle which injects premixed fuel, and
a first main nozzle and a second main nozzle which are provided around the pilot nozzle and inject premixed fuel; and
a combustor control device according to claim 10 .
16 . A gas turbine system comprising:
a gas turbine provided with a combustor comprising
a pilot nozzle which injects premixed fuel, and
a first main nozzle and a second main nozzle which are provided around the pilot nozzle and inject premixed fuel; and
a combustor control device according to claim 11 .
17 . A gas turbine system comprising:
a gas turbine provided with a combustor comprising
a pilot nozzle which injects premixed fuel, and
a first main nozzle and a second main nozzle which are provided around the pilot nozzle and inject premixed fuel; and
a combustor control device according to claim 12 .
18 . A gas turbine combustor control method comprising:
a load interruption detection step of detecting load interruption of a gas turbine;
a pilot nozzle flow rate control step of increasing the amount of premixed fuel supplied to a pilot nozzle, based on detection of the load interruption;
a first main nozzle flow rate control step of reducing the amount of premixed fuel supplied to a first main nozzle, based on detection of the load interruption; and
a second main nozzle flow rate control step of reducing the amount of premixed fuel supplied to a second main nozzle to a predetermined amount, based on detection of the load interruption, and then further reducing the amount of premixed fuel supplied after the elapse of a predetermined time.