Abstract: Embodiments of the disclosure provide a method for controlling a power generation system during on-line maintenance. The method includes operating the power generation system in a first maintenance mode, which causes a controller of the power generation system to disable an automated response to at least one operational fault of the power generation system; monitoring a risk parameter of the power generation system or at least one sensor within the power generation system while operating the power generation system in the first maintenance mode; and operating the power generation system in a second maintenance mode in response to detecting an override command, an elapsed time exceeding a time limit, or the monitored risk parameter exceeding a safety threshold. The second maintenance mode causes the controller of the power generation system to enable the automated response to the at least one operational fault of the power generation system.

Abstract: Embodiments of the disclosure provide a method for controlling a power generation system during on-line maintenance. The method includes operating the power generation system in a first maintenance mode, which causes a controller of the power generation system to disable an automated response to at least one operational fault of the power generation system; monitoring a risk parameter of the power generation system or at least one sensor within the power generation system while operating the power generation system in the first maintenance mode; and operating the power generation system in a second maintenance mode in response to detecting an override command, an elapsed time exceeding a time limit, or the monitored risk parameter exceeding a safety threshold. The second maintenance mode causes the controller of the power generation system to enable the automated response to the at least one operational fault of the power generation system.

Abstract: A method for determining the flow rate of combustible fluid injected into a combustion chamber (120) of a turbine (100) includes determining the cross section of the orifice of the at least one injector (112, 113, 114, 115) through which the combustible fluid is injected into the combustion chamber (120). The pressure of the combustible fluid upstream of the orifice of the injector (112, 113, 114, 115) is determined. The pressure downstream of the orifice of the injector (112, 113, 114, 115) is determined. The flow rate of combustible fluid flowing through the orifice of the at least one injector (112, 113, 114, 115) is determined.

Abstract: A gas supply system of a gas turbine and a method for controlling an operation of the gas supply system. A gas supply system includes a first valve connected in series to a set of second valves that are in parallel with each other. At least one second valve from the set of second valves is connected to a combustion chamber of the gas turbine. A degree of opening of the first valve and the at least one second valve is changed to in a manner that controls a total mass flow of gas output by the set of second valves during the change in the degree of opening.

Abstract: A method of testing a gas turbine is provided. The gas turbine includes a first compressor and an expansion turbine coupled by a drive shaft. The method includes operating the gas turbine and a second compressor at a first steady load and a first steady drive shaft speed. The second compressor is rigidly coupled to the drive shaft. The method also includes changing a load of the second compressor by a known amount, and measuring a time required for the gas turbine to stabilize at a second steady load and a second steady drive shaft speed in response to the changed load of the second compressor.

Abstract: A gas supply system of a gas turbine and a method for controlling an operation of the gas supply system. A gas supply system includes a first valve connected in series to a set of second valves that are in parallel with each other. At least one second valve from the set of second valves is connected to a combustion chamber of the gas turbine. A degree of opening of the first valve and the at least one second valve is changed to in a manner that controls a total mass flow of gas output by the set of second valves during the change in the degree of opening.

Abstract: A method of testing a gas turbine is provided. The gas turbine includes a first compressor and an expansion turbine coupled by a drive shaft. The method includes operating the gas turbine and a second compressor at a first steady load and a first steady drive shaft speed. The second compressor is rigidly coupled to the drive shaft. The method also includes changing a load of the second compressor by a known amount, and measuring a time required for the gas turbine to stabilize at a second steady load and a second steady drive shaft speed in response to the changed load of the second compressor.

Abstract: When driven by a variable speed prime mover, a generator system provides relatively constant frequency AC power by independently controlling the main rotor flux rotational speed. The generator system includes an exciter stator that induces current in the exciter rotor windings at a desired frequency and phasing. The exciter rotor windings are electrically connected to and located in a common core as the main rotor windings to provide two-phase excitation current to the main rotor windings. The exciter stator winding is also located in a common core as the main generator stator windings. Excitation is supplied to the exciter stator from an exciter controller, which controls the frequency and phasing of the exciter excitation, based on the rotational speed and rotor position of the generator, to maintain a constant output frequency.