Gas turbine control device, gas turbine control method, and gas turbine control program

The gas turbine control device addresses combustion oscillation during rapid startup by dividing fuel supply nozzles into groups and adjusting fuel ratios using a base index and correction value, ensuring a control margin and suppressing oscillation for stable operation.

JP7763938B2Active Publication Date: 2025-11-04MITSUBISHI HEAVY IND LTD
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Patent Information

Application Number
JP2024516211
Authority / Receiving Office
JP · JP
Patent Type
Patents
Current Assignee / Owner
Priority Date
2022-04-20
Filing Date
2023-04-11
Publication Date
2025-11-04
Estimated Expiration
2043-04-11

AI Technical Summary

Technical Problem

Gas turbines experience combustion oscillation during rapid startup when load is added before the fuel temperature has sufficiently risen, increasing the risk of tripping, especially with the rise of renewable energy sources in power grids requiring rapid startup capabilities.

Method used

A gas turbine control device and method that divides fuel supply nozzles into groups, using a base index and correction value to control fuel supply ratios, ensuring a control margin by adjusting these ratios to zero after a predetermined time post-startup, thereby suppressing combustion oscillation.

Benefits of technology

Effectively suppresses combustion oscillation during rapid startup by ensuring a control margin, allowing smooth transition to normal operation as fuel temperature rises, reducing the risk of turbine trip.

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Abstract

A gas turbine control device of the present disclosure controls a gas turbine in which a combustor is configured in a state where a plurality of fuel supply nozzles for supplying fuel are separated into a first group and a second group. This device, on the basis of the operating state of the gas turbine, calculates a control parameter base index relating to the ratio of the amount of fuel supplied by the second group to the amount of fuel supplied by the first group. The base index is corrected using a correction value calculated on the basis of the operating state of the gas turbine. The amounts of fuel supplied by the first group and the second group are each controlled on the basis of a control parameter obtained by correcting the base index using the correction value. This correction value is calculated so that the absolute value thereof decreases to zero after the gas turbine has been started up and a prescribed length of time has passed since load addition to the gas turbine.
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