Abstract: A flow rate per unit time of fuel fed to a gas turbine is calculated. A flow rate per unit time of air fed to the gas turbine is calculated. A turbine inlet temperature is calculated through use of a physical model formula expressing a relationship of input and output of thermal energy relating to a combustor of the gas turbine. A fuel distribution ratio for each of a plurality of fuel supply systems connected to the combustor is calculated based on the turbine inlet temperature.

Abstract: According to an embodiment, a turbine stage sealing mechanism reduces leak flow, which bypasses a working fluid flow path, between a rotating part and a stationary part in each turbine stage of a gas turbine. A radially inner side end portion of the stationary part is formed to be on a circle centered at a center axis of the rotating part under a predetermined operating condition of the gas turbine.

Abstract: A fuel control device includes a combustion temperature estimation value calculation unit that calculates a temperature estimation value when a mixture of fuel and inflow air is burned using an atmospheric condition, an opening degree command value of a valve that controls the amount of air that is mixed with the fuel and burned, and an output prediction value calculated on the basis of a fuel control signal command value used for calculation of a total fuel flow rate flowing through a plurality of fuel supply systems, a fuel distribution command value calculation unit that calculates a fuel distribution command value indicating a distribution of fuel output from the fuel supply systems based on the temperature estimation value, and outputs the fuel distribution command value, and a valve opening degree calculation unit that calculates each valve opening degree of a fuel flow rate control valve of the fuel supply systems.

Abstract: A gas turbine apparatus includes a turbine configured to be driven by a combustion gas from a combustor, an exhaust passage, an extraction line configured to extract a fluid from a combustor casing, a cooling part disposed in the extraction line and configured to cool the fluid, a return line for returning the fluid from the cooling part to an inside of the combustor casing, the return line being connected to the extraction line downstream of the cooling part, a bypass line for introducing the fluid from the cooling part to the exhaust passage by bypassing the turbine, the bypass line branching from the return line, and a communication state switching part for controlling a communication state between the extraction line and the combustor casing via the return line, and a communication state between the extraction line and the exhaust passage via the bypass line.

Abstract: A fuel control device includes a combustion temperature estimation value calculation unit that calculates a temperature estimation value when a mixture of fuel and inflow air is burned using an atmospheric condition, an opening degree command value of a valve that controls the amount of air that is mixed with the fuel and burned, and an output prediction value calculated on the basis of a fuel control signal command value used for calculation of a total fuel flow rate flowing through a plurality of fuel supply systems, a fuel distribution command value calculation unit that calculates a fuel distribution command value indicating a distribution of fuel output from the fuel supply systems based on the temperature estimation value, and outputs the fuel distribution command value, and a valve opening degree calculation unit that calculates each valve opening degree of a fuel flow rate control valve of the fuel supply systems.

Abstract: According to an embodiment, a turbine stator blade disposed in a working fluid flow path in a casing of a gas turbine, includes: a blade effective part disposed in the working fluid flow path; an outer circumferential sidewall having a plate-shaped part that is connected to a radially outer end portion of the blade effective part, and hooks each extending radially outward and circumferentially from the plate-shaped part and having a tip engaged with the casing; and an inner circumferential sidewall connected to a radially inner end portion of the blade effective part. At least one slit is formed at the rear hook or front hook to divide the hook in a circumferential direction, and the hook has a seal member to seal the slit.

Abstract: A first fuel flow rate command value indicating a command value of a fuel input amount is calculated so that an output of a gas turbine matches a target output. An upper limit value of the first fuel flow rate command value is calculated based on a deviation obtained by subtracting, from an estimated value of a turbine inlet temperature of the gas turbine, a second limit value relating to the estimated value set such that the estimated value does not exceed a first limit value of the turbine inlet temperature.

Abstract: A control device for a gas turbine include: a target value calculation part configured to calculate a control target value being a target value of an output of the gas turbine; and a command value calculation part configured to calculate a fuel command value on the basis of a deviation between the control target value and an actual output value of the gas turbine. The target value calculation part is configured to: set the control target value to a value which is greater than an output demand value of the gas turbine immediately before a difference between the output demand value and the actual output value becomes not greater than a threshold; and subtract the control target value from the value after the difference becomes not greater than the threshold.

Abstract: A turbine rotor of an embodiment includes a rotor body portion having turbine discs in plural stages in an axial direction protruding radially outside from an outer peripheral surface of the rotor body portion over a circumferential direction. The turbine rotor includes a plurality of axial passages, through which a cooling medium flows, formed at the rotor body portion radially outside than a center axis of the turbine rotor and radially inside than an outer peripheral surface of the rotor body portion in the axial direction; an introduction passage introducing the cooling medium into each of the axial passages; and discharge passages that penetrate from each of the axial passages to the outer peripheral surface of the rotor body portion to discharge the cooling medium.

Abstract: A gas turbine control device includes a first estimation unit configured to estimate a first temperature which is a first turbine inlet temperature estimation value based on a first model which is a physical model using a fuel flow rate to a gas turbine; a second estimation unit configured to estimate a second temperature which is a second turbine inlet temperature estimation value based on a second model which is a physical model using an exhaust gas temperature of the gas turbine; and a correction unit configured to correct the first temperature based on the second temperature to calculate a third turbine inlet temperature estimation value.

Abstract: According to an embodiment, a turbine stator blade disposed in a working fluid flow path in a casing of a gas turbine, includes: a blade effective part disposed in the working fluid flow path; an outer circumferential sidewall having a plate-shaped part that is connected to a radially outer end portion of the blade effective part, and hooks each extending radially outward and circumferentially from the plate-shaped part and having a tip engaged with the casing; and an inner circumferential sidewall connected to a radially inner end portion of the blade effective part. At least one slit is formed at the rear hook or front hook to divide the hook in a circumferential direction, and the hook has a seal member to seal the slit.

Abstract: According to an embodiment, a turbine stator blade disposed in a working fluid flow path in a casing of a gas turbine, comprises: a blade effective part disposed in the working fluid flow path; an outer ring sidewall having a plate-shaped portion connecting to a radially outer end portion of the blade effective part, a front hook extending radially outward and circumferentially from the plate-shaped portion and having a tip fitting with the casing, a rear hook extending radially outward and circumferentially from the plate-shaped portion and having a tip fitting with the casing; and a reinforcing member that maintains an interval between the front hook and the rear hook; and an inner ring sidewall connected to a radially inner end portion of the blade effective part.

Abstract: A gas turbine apparatus includes a turbine configured to be driven by a combustion gas from a combustor, an exhaust passage, an extraction line configured to extract a fluid from a combustor casing, a cooling part disposed in the extraction line and configured to cool the fluid, a return line for returning the fluid from the cooling part to an inside of the combustor casing, the return line being connected to the extraction line downstream of the cooling part, a bypass line for introducing the fluid from the cooling part to the exhaust passage by bypassing the turbine, the bypass line branching from the return line, and a communication state switching part for controlling a communication state between the extraction line and the combustor casing via the return line, and a communication state between the extraction line and the exhaust passage via the bypass line.

Abstract: A gas turbine control device includes a detection value acquisition unit that acquires a detection value of at least one of a supply amount of fuel, pressure of compressed air, and electric power generated by a generator; a flue gas temperature acquisition unit that acquires a flue gas temperature detection value; a combustion gas temperature estimate value calculation unit that calculates a combustion gas temperature estimate value based on the detection value; a correction term acquisition unit that calculates a correction term based on a ratio between the combustion gas temperature estimate value and the flue gas temperature detection value; a corrected combustion gas temperature estimate value calculation unit that corrects the combustion gas temperature estimate value using the correction term to calculate a corrected combustion gas temperature estimate value; and a gas turbine controller that controls the gas turbine based on the corrected combustion gas temperature estimate value.

Abstract: A turbine rotor of an embodiment includes a rotor body portion having turbine discs in plural stages in an axial direction protruding radially outside from an outer peripheral surface of the rotor body portion over a circumferential direction. The turbine rotor includes a plurality of axial passages, through which a cooling medium flows, formed at the rotor body portion radially outside than a center axis of the turbine rotor and radially inside than an outer peripheral surface of the rotor body portion in the axial direction; an introduction passage introducing the cooling medium into each of the axial passages; and discharge passages that penetrate from each of the axial passages to the outer peripheral surface of the rotor body portion to discharge the cooling medium.

Abstract: A control device for a gas turbine include: a target value calculation part configured to calculate a control target value being a target value of an output of the gas turbine; and a command value calculation part configured to calculate a fuel command value on the basis of a deviation between the control target value and an actual output value of the gas turbine. The target value calculation part is configured to: set the control target value to a value which is greater than an output demand value of the gas turbine immediately before a difference between the output demand value and the actual output value becomes not greater than a threshold; and subtract the control target value from the value after the difference becomes not greater than the threshold.

Abstract: A flow rate per unit time of fuel fed to a gas turbine is calculated. A flow rate per unit time of air fed to the gas turbine is calculated. A turbine inlet temperature is calculated through use of a physical model formula expressing a relationship of input and output of thermal energy relating to a combustor of the gas turbine. A fuel distribution ratio for each of a plurality of fuel supply systems connected to the combustor is calculated based on the turbine inlet temperature.

Abstract: Provided is a control device of a gas turbine including a compressor, a combustor, and a turbine. The control device executes load control of allowing an operation control point for operation control of a gas turbine to vary in response to a load of the gas turbine. The operation of the gas turbine is controlled on the basis of a rated temperature adjustment line for temperature adjustment control of a flue gas temperature at a predetermined load to a rated flue gas temperature at which performance of the gas turbine becomes rated performance, a preceding setting line for setting of the flue gas temperature at the predetermined load to a preceding flue gas temperature that becomes lower in precedence to the rated flue gas temperature, and a limit temperature adjustment line for temperature adjustment control.

Abstract: A cooling system includes: a high pressure bleed line configured to bleed high pressure compressed air from a first bleed position of a compressor and to send the air to a first hot part; a low pressure bleed line configured to bleed low pressure compressed air from a second bleed position of the compressor and to send the air to a second hot part; an orifice provided in the low pressure bleed line; a connecting line configured to connect the high pressure bleed line and the low pressure bleed line; a first valve provided in the connecting line; a bypass line configured to connect the connecting line and the low pressure bleed line; and a second valve provided in the bypass line.

Abstract: A first fuel flow rate command value indicating a command value CSO of a fuel input amount is calculated so that the output of a gas turbine matches a target output. An upper limit value of the first fuel flow rate command value is calculated. The upper limit value of the first fuel flow rate command value is calculated on the basis of a deviation obtained by subtracting from an estimated value of the turbine inlet temperature of the gas turbine a second limit value relating to the estimated value set such that the estimated value does not exceed the first limit value of the turbine inlet temperature.