Gas turbine combustion control device and combustion control method and program therefor

A gas turbine combustion control method for a gas turbine including:

• a compressor having inlet guide vanes;
• a combustor having a plurality of fuel nozzles;
• a turbine;
• a bleed air pipe through which bleed air from a casing is returned to an inlet of an air intake facility;
• an air bleed valve that is mounted on the bleed air pipe and regulates the amount of bleed air extracted;
• and
• a gas turbine combustion control device configured to set fuel distribution ratios for circuits of fuel supplied to the combustor, the gas turbine combustion control method comprising the steps of:
• calculating first interpolated data equivalent to a turbine inlet temperature or a turbine inlet temperature-equivalent control variable in a first operation mode computed on the basis of input data on the first operation mode that is an operation mode in which the gas turbine does not perform anti-icing operation;
• calculating second interpolated data equivalent to a turbine inlet temperature or a turbine inlet temperature-equivalent control variable in a second operation mode computed on the basis of input data on the second operation mode that is an anti-icing operation mode in which a constant amount of bleed air is set and part of the bleed air from the casing is circulated to the air intake facility;
• using the first interpolated data and the second interpolated data, calculating a modified turbine inlet temperature or a modified turbine inlet temperature-equivalent control variable in a predetermined operation mode on the basis of a specific parameter determined by the amount of bleed air extracted in the predetermined operation mode that is an anti-icing operation mode in which an amount of bleed air required for anti-icing operation is selected and that amount of bleed air is circulated to the air intake facility;
• calculating the fuel distribution ratios for the respective fuel circuits in the predetermined operation mode on the basis of the modified turbine inlet temperature or the modified turbine inlet temperature-equivalent control variable;
• and
• setting valve openings for the respective fuel circuits on the basis of the fuel distribution ratios.

A gas turbine combustion control method for a gas turbine including:

• a compressor having inlet guide vanes;
• a combustor having a plurality of fuel nozzles;
• a turbine;
• a bleed air pipe through which bleed air from a casing is returned to an inlet of an air intake facility;
• an air bleed valve that is mounted on the bleed air pipe and regulates the amount of bleed air extracted;
• and
• a gas turbine combustion control device configured to set fuel distribution ratios for circuits of fuel supplied to the combustor, the gas turbine combustion control method comprising the steps of:
• calculating first interpolated output data corresponding to a turbine inlet temperature related to an output during no load operation on the basis of input data on a first operation mode that is an operation mode in which the gas turbine does not perform anti-icing operation;
• calculating second interpolated output data corresponding to a turbine inlet temperature related to an output during rated load operation on the basis of input data on the first operation mode;
• calculating an output correction factor on the basis of a specific parameter determined by the amount of bleed air extracted in a predetermined operation mode that is an anti-icing operation mode in which an amount of bleed air required for anti-icing operation is selected and that amount of bleed air is circulated to the air intake facility;
• calculating first modified interpolated output data by modifying the first interpolated output data on the basis of the output correction factor;
• calculating second modified interpolated output data by modifying the second interpolated output data on the basis of the output correction factor;
• using the first modified interpolated output data and the second modified interpolated output data, calculating a turbine inlet temperature-equivalent control variable on the basis of a turbine output in the predetermined operation mode;
• calculating the fuel distribution ratios for the respective fuel circuits in the predetermined operation mode on the basis of the turbine inlet temperature-equivalent control variable;
• and
• setting valve openings for the respective fuel circuits on the basis of the fuel distribution ratios.

A gas turbine combustion control method for a gas turbine including:

• a compressor having inlet guide vanes;
• a combustor having a plurality of fuel nozzles;
• a turbine;
• a bleed air pipe through which bleed air from a casing is returned to an inlet of an air intake facility;
• an air bleed valve that is mounted on the bleed air pipe and regulates the amount of bleed air extracted;
• and
• a gas turbine combustion control device configured to set fuel distribution ratios for circuits of fuel supplied to the combustor, the gas turbine combustion control method comprising the steps of:
• creating a database on the basis of input data on a first operation mode that is an operation mode in which the gas turbine does not perform anti-icing operation, and a database on the basis of input data on a second operation mode that is an anti-icing operation mode in which a constant amount of bleed air is set and part of the bleed air from the casing is circulated to the air intake facility;
• calculating first interpolated data equivalent to a turbine inlet temperature or a turbine inlet temperature-equivalent control variable in the first operation mode on the basis of the database;
• calculating second interpolated data equivalent to a turbine inlet temperature or a turbine inlet temperature-equivalent control variable in the second operation mode on the basis of the database;
• using the first interpolated data and the second interpolated data, calculating a modified turbine inlet temperature or a modified turbine inlet temperature-equivalent control variable in a predetermined operation mode on the basis of a specific parameter determined by the amount of bleed air extracted in the predetermined operation mode that is an anti-icing operation mode in which an amount of bleed air required for anti-icing operation is selected and that amount of bleed air is circulated to the air intake facility;
• calculating the fuel distribution ratios for the respective fuel circuits in the predetermined operation mode on the basis of the modified turbine inlet temperature or the modified turbine inlet temperature-equivalent control variable;
• and
• setting valve openings for the respective fuel circuits on the basis of the fuel distribution ratios.