A maximum output creator is provided with: a temperature reception unit that receives an intake temperature, which is the temperature of air taken in by a compressor of a gas turbine; a change reception unit that receives the details of a change to a maximum opening degree in an intake quantity adjuster of the compressor; a basic maximum output computation unit that determines a basic maximum output of the gas turbine on the basis of the intake temperature received by the temperature reception unit; a coefficient creation unit that creates a maximum output correction coefficient for correcting the basic maximum output on the basis of the details of the change to the maximum opening degree received by the change reception unit and the intake temperature received by the temperature reception unit; and a maximum output correction unit that corrects the basic maximum output using the maximum output correction coefficient.

A method for controlling a gap minimization for an adjustable gap between a rotor and a housing of a gas turbine carried out on the basis of a correlation extracted from simulation data. If the actual value (P.sub.I) lies below the lower threshold (P.sub.U), the gap minimization is deactivated, whereas if the actual value lies above the upper threshold (P.sub.O), the gap minimization is activated. The gap minimization is activated between the thresholds (P.sub.U, P.sub.O) if the actual value lies above the threshold (P.sub.G) but is deactivated if the actual value (P.sub.I) lies below the threshold (P.sub.G).

A method for controlling a gap minimization for an adjustable gap between a rotor and a housing of a gas turbine carried out on the basis of a correlation extracted from simulation data. If the actual value (P.sub.I) lies below the lower threshold (P.sub.U), the gap minimization is deactivated, whereas if the actual value lies above the upper threshold (P.sub.O), the gap minimization is activated. The gap minimization is activated between the thresholds (P.sub.U, P.sub.O) if the actual value lies above the threshold (P.sub.G) but is deactivated if the actual value (P.sub.I) lies below the threshold (P.sub.G).

A gas turbine combined cycle (GTCC) power generation plant (100) equipped with a control unit which performs a load reduction following operation with respect to a fuel adjustment valve (Vd), a main steam valve (V1), and a bypass valve (V4), wherein, when a load reduction request for reducing a GTCC load target value has been input in a closed bypass operation, the degree of opening of the fuel adjustment valve (Vd) is reduced in accordance with the target value while the main steam valve (V1) is in an open state, and the bypass valve (V4) is placed in an open state, after which the bypass valve (V4) is placed in the closed state when the GTCC load reaches the target value.

A gas turbine combined cycle (GTCC) power generation plant (100) equipped with a control unit which performs a load reduction following operation with respect to a fuel adjustment valve (Vd), a main steam valve (V1), and a bypass valve (V4), wherein, when a load reduction request for reducing a GTCC load target value has been input in a closed bypass operation, the degree of opening of the fuel adjustment valve (Vd) is reduced in accordance with the target value while the main steam valve (V1) is in an open state, and the bypass valve (V4) is placed in an open state, after which the bypass valve (V4) is placed in the closed state when the GTCC load reaches the target value.

A gas turbine engine with a compressor supplying compressed air. A combustor receives the compressed air and fuel and generates a flow of combusted gas. A turbine receives a core flow of the combusted gas to rotate a turbine rotor. A turbine inlet nozzle directs the combusted gas to the turbine rotor. Vanes are disposed in the turbine inlet nozzle and rotate to vary a flow area through which the core flow passes. The vanes adjust a pressure ratio of the gas turbine engine to compensate for changing operational requirements of the gas turbine engine by rotating to positions matching the changing operational requirements.

A system and method for determining performance of a turbine engine, and operation thereof. The system and method includes a plurality of sensors and one or more computing devices executing operations including acquiring a plurality of parameter sets each corresponding to a plurality of engine conditions in which each parameter set corresponding to each engine condition indicates a health condition at a plurality of locations at the engine; comparing the plurality of parameter sets to determine a health condition corresponding to a location at the engine; and generating a health condition prediction at the engine based on the compared parameters.

A system and method for determining performance of a turbine engine, and operation thereof. The system and method includes a plurality of sensors and one or more computing devices executing operations including acquiring a plurality of parameter sets each corresponding to a plurality of engine conditions in which each parameter set corresponding to each engine condition indicates a health condition at a plurality of locations at the engine; comparing the plurality of parameter sets to determine a health condition corresponding to a location at the engine; and generating a health condition prediction at the engine based on the compared parameters.

An aeromechanical identification system for turbomachine includes at least one actuator mounted on a stationary structure to excite rotatable airfoils. At least one sensor is mounted proximate the airfoils for measuring a response of the airfoils responsive to excitation from the at least one actuator. A controller is configured to determine a damping characteristic of an aeromechanical mode of the rotating airfoils based on the excitation and the response. A gas turbine engine and a method of determining a flutter boundary for an airfoil of a turbomachine are also disclosed.

An aeromechanical identification system for turbomachine includes at least one actuator mounted on a stationary structure to excite rotatable airfoils. At least one sensor is mounted proximate the airfoils for measuring a response of the airfoils responsive to excitation from the at least one actuator. A controller is configured to determine a damping characteristic of an aeromechanical mode of the rotating airfoils based on the excitation and the response. A gas turbine engine and a method of determining a flutter boundary for an airfoil of a turbomachine are also disclosed.