Gas turbine, gas-turbine control device, and gas turbine operation method

A gas turbine with a control device configured to control an operation of the gas turbine which is configured to acquire rotational power by supplying fuel to a combustion chamber and burning the fuel in compressed air compressed by a compressor and supplying generated combustion gas to a turbine, the gas turbine including:

• means for pressurizing a portion of the compressed air compressed by the compressor, the portion of the compressed air having flowed into the means for pressurizing;
• means for cooling the combustion chamber with at least a first part of the portion of the compressed air pressurized by the means for pressurizing;
• means for regulating turbine temperature to regulate a temperature of a stationary member of the turbine with at least a second part of the portion of the compressed air pressurized by the means for pressurizing;
• a combustion chamber supply channel through which at least the first part of the portion of the compressed air is configured to flow from the means for pressurizing to the means for cooling the combustion chamber;
• a turbine supply channel through which at least the second part of the portion of the compressed air is configured to flow from the means for pressurizing to the means for regulating turbine temperature;
• means for heating at least the second part of the portion of the compressed air, the means for heating at least the second part of the portion of the compressed air being provided in the turbine supply channel;
• a connecting supply channel through which at least the second part of the portion of the compressed air is configured to flow from the means for regulating turbine temperature to the means for cooling the combustion chamber;
• and
• a flow rate regulating mechanism provided in the connecting supply channel;
• wherein, in a rated operation mode, which is a control mode during rating of the gas turbine, the control device is configured to control the flow rate regulating mechanism to cause at least the second part of the portion of the compressed air to flow from the means for regulating turbine temperature into the means for cooling the combustion chamber.

An operation method for a gas turbine configured to acquire rotational power by supplying fuel to a combustion chamber and burning the fuel in compressed air compressed by a compressor and supplying generated combustion gas to a turbine, the gas turbine including:

• means for pressurizing a portion of the compressed air compressed by the compressor, the portion of the compressed air having flowed into the means for pressurizing;
• means for cooling the combustion chamber with at least a first part of the portion of the compressed air pressurized by the means for pressurizing;
• means for regulating turbine temperature to regulate a temperature of a stationary member of the turbine with at least a second part of the portion of the compressed air pressurized by the means for pressurizing;
• a combustion chamber supply channel through which at least the first part of the portion of the compressed air is configured to flow from the means for pressurizing to the means for cooling the combustion chamber;
• a turbine supply channel through which at least the second part of the portion of the compressed air is configured to flow from the means for pressurizing to the means for regulating turbine temperature;
• means for heating at least the second part of the portion of the compressed air, the means for heating at least the second part of the portion of the compressed air being provided in the turbine supply channel;
• a connecting supply channel through which at least the second part of the portion of the compressed air is configured to flow from the means for regulating turbine temperature to the means for cooling the combustion chamber;
• and
• a flow rate regulating mechanism provided in the connecting supply channel;
• wherein:
• in a rated operation of the gas turbine, the flow rate regulating mechanism is controlled to cause at least the second part of the portion of the compressed air to flow from the means for regulating turbine temperature into the means for cooling the combustion chamber;
• the stationary member includes a blade ring;
• the means for regulating turbine temperature includes a blade ring inner channel defined in the blade ring;
• and
• the connecting supply channel is configured to pass at least the second part of the portion of the compressed air to the means for cooling the combustion chamber from the blade ring inner channel defined in the blade ring at the rated operation of the gas turbine.