Gas turbine operation method and gas turbine equipment capable of executing same

Gas turbine equipment comprising:

• a compressor capable of compressing air to generate compressed air;
• a combustor capable of burning fuel in the compressed air to generate combustion gas;
• a turbine capable of being driven by the combustion gas;
• and
• a fuel supply system capable of supplying a first fuel and a second fuel to the combustor, wherein
• the combustor includes a cylinder in which the fuel is capable of being burned, and a plurality of burners capable of injecting the fuel into the cylinder together with the compressed air,
• the plurality of burners include a first burner and a plurality of second burners excluding the first burner,
• the first burner and the plurality of second burners each include an air flow channel frame capable of allowing the air to flow and capable of injecting the air into the cylinder, and a nozzle capable of injecting the fuel into the air flow channel frame,
• the fuel supply system includes
• a first fuel line connected to a supply source of the first fuel and through which the first fuel is capable of flowing,
• a second fuel line connected to a supply source of the second fuel and through which the second fuel is capable of flowing,
• a first fuel valve provided in the first fuel line,
• a second fuel valve provided in the second fuel line,
• a header line through which the first fuel and the second fuel are capable of flowing,
• branch lines that branch from the header line to each of the plurality of burners, and
• a gate valve provided in the header line and capable of partitioning the header line into a first header portion and a second header portion,
• first branch lines that are some of the respective branch lines of the plurality of burners branch from the first header portion,
• the first branch lines are connected to a first nozzle that is the nozzle of the first burner,
• a plurality of second branch lines excluding the first branch lines among the respective branch lines of the plurality of burners branch from the second header portion,
• each of the plurality of second branch lines is connected to a second nozzle that is the nozzle of each of the plurality of second burners,
• the first fuel line is connected to the first header portion, and
• the second fuel line is connected to the second header portion.