Abstract: A method is disclosed for operating a gas turbine having a compressor, a combustor, a turbine downstream of the combustor, and a total number of turbine outlet temperature measurements. The method includes locally measuring the turbine outlet temperature of the turbine with the turbine outlet temperature measurements of the respective turbine, and averaging measured temperatures of the selected turbine outlet temperature measurements to obtain an average turbine outlet temperature. The gas turbine operation is controlled depending on the determined average turbine outlet temperature.

Abstract: The invention relates to a method for detecting a fuel leakage in the fuel distribution system between a fuel control valve and at least one burner of a gas turbine during the operation of the gas turbine. In order to detect a fuel leakage, the fuel consumption is approximated in accordance with the mechanical power of the gas turbine, the fuel amount fed to the fuel distribution system is determined, and the leakage flow is determined from the difference between the fed fuel amount and the fuel consumption. The invention further relates to a gas turbine for performing such a method.

Abstract: A method for operating a gas turbine (11) having a compressor (12), a turbine (14) and a combustor (13) with a pilot burner group (15a), a rich premix burner group (15b) and a lean premix burner group (15c), under changing composition of the incoming fuel gas (16), includes the steps of: continuously measuring, in real time, the composition of the fuel gas (16); and controlling the operation of the gas turbine (11) and the combustion of the burners (15a-c) by using the real time fuel gas composition measurements.

Abstract: The present disclosure refers to a method for operating a gas turbine having a compressor, a combustor, a turbine downstream of the combustor, and a total number of turbine outlet temperature measurement sensors. The method can include supplying a first fuel flow to one of the burners of one combustor, which is smaller than a second fuel flow to another one of the burners the same combustor, selecting a number of turbine outlet temperature measurements which is smaller than a total number of the turbine outlet temperature measurement sensors, and averaging measured temperatures of the selected turbine outlet temperature measurements to obtain an trimmed turbine outlet temperature which is used for controlling operation of the gas turbine.

Abstract: A method for operating a power plant is disclosed. The method comprises providing at least one shaft power thereby providing a total shaft power, driving at least one generator thereby providing a total electric power output, providing a first share of the total electric power output to a grid as a grid power output, and providing a second share of the total electric power output to at least one power consumer. The grid power output is modulated independently from the total electric power output and the total shaft power output in modulating the second share of the total electric power output.

Abstract: A method is disclosed for operating a gas turbine having a compressor, a combustor, a turbine downstream of the combustor, and a total number of turbine outlet temperature measurements. The method includes locally measuring the turbine outlet temperature of the turbine with the turbine outlet temperature measurements of the respective turbine, and averaging measured temperatures of the selected turbine outlet temperature measurements to obtain an average turbine outlet temperature. The gas turbine operation is controlled depending on the determined average turbine outlet temperature.

Abstract: The invention refers to a method for controlling part load operation of a gas turbine comprising a controller wherein a load set point of the controller is greater or equal a minimum load set point. The minimum load set point depends on a hot gas temperature that is calculated based on a hot gas temperature model.

Abstract: The invention concerns a method of operating a gas turbine with staged and/or sequential combustion. The burners of a second stage or a second combustor are singularly and sequentially switched on during loading and switched off during de-loading. The total fuel mass flow and the compressor inlet guide vanes are adjusted at the same time to allow controlling gas turbine operation temperatures and engine power with respect to the required CO emission target.

Abstract: A method for operating a gas turbine includes supplying fuel via at least one control valve regulated using an open-loop control system based on a predetermined load setpoint value. A valve stroke control command (scmd) is generated based on a fuel mass flow control command (mcmd) using a mass flow-valve stroke converter. The valve stroke control command (scmd) is compared with a valve stroke limit value (min{slim1, slim2}) using a variable pressure regulator. A load limit value is generated if the valve stroke control command (scmd) exceeds the valve stroke limit value (min{slim1, slim2}) to reduce the load setpoint value. Operation of the gas turbine is stabilized using a low limit value (xlim) of a pressure drop ratio (x), wherein the pressure drop ratio (x) is a quotient of a pressure drop (dp) which occurs at the control valve and of a pressure (p1) upstream of the control valve.

Abstract: The invention relates to a method for detecting a fuel leakage in the fuel distribution system between a fuel control valve and at least one burner of a gas turbine during the operation of the gas turbine. In order to detect a fuel leakage, the fuel consumption is approximated in accordance with the mechanical power of the gas turbine, the fuel amount fed to the fuel distribution system is determined, and the leakage flow is determined from the difference between the fed fuel amount and the fuel consumption. The invention further relates to a gas turbine for performing such a method.

Abstract: The disclosure relates to a method for operating a gas turbine plant which is supplied with a fuel gas via a compressor station. The compressor station includes a compressor which compresses the fuel gas which is fed via a gas feed line and delivers it via at least one control valve to a combustion chamber of the gas turbine plant. A bypass system is arranged in parallel to the compressor via which fuel gas can be directed in a switchable manner past the compressor to the at least one control valve. An energy-saving operation can be achieved in a simple manner by continuously measuring the fuel gas pressure at the outlet of the at least one control valve. A minimum fuel gas pressure, which is desired (e.g., necessary) for operation of the gas turbine, at the inlet of the at least one control valve is determined from the measured pressure values in each case.

Abstract: A method for operating a gas turbine (11) having a compressor (12), a turbine (14) and a combustor (13) with a pilot burner group (15a), a rich premix burner group (15b) and a lean premix burner group (15c), under changing composition of the incoming fuel gas (16), includes the steps of: continuously measuring, in real time, the composition of the fuel gas (16); and controlling the operation of the gas turbine (11) and the combustion of the burners (15a-c) by using the real time fuel gas composition measurements.

Abstract: A method for operating a gas turbine includes supplying fuel via at least one control valve regulated using an open-loop control system based on a predetermined load setpoint value. A valve stroke control command (scmd) is generated based on a fuel mass flow control command (mcmd) using a mass flow-valve stroke converter. The valve stroke control command (scmd) is compared with a valve stroke limit value (min{slim1, slim2}) using a variable pressure regulator. A load limit value is generated if the valve stroke control command (scmd) exceeds the valve stroke limit value (min{slim1, slim2}) to reduce the load setpoint value. Operation of the gas turbine is stabilized using a low limit value (xlim) of a pressure drop ratio (x), wherein the pressure drop ratio (x) is a quotient of a pressure drop (dp) which occurs at the control valve and of a pressure (p1) upstream of the control valve.

Abstract: A method for protecting a gas turbine installation from overheating and for detecting flame extinction in the combustion chamber is described, in which air is compressed in a compressor unit and, after being admixed with fuel, is ignited in the form of a fuel/air mixture in a combustion chamber and is burnt, thus giving rise to a hot gas flow which sets a turbine stage in rotation downstream of the combustion chamber so as to perform expansion work. The pressure upstream of the turbine stage, that is the pressure pk of the compressed air in the plenum and/or the pressure within the combustion chamber pcom, is measured, in that a time change of the measured pressure, what is known as the pressure gradient ({dot over (p)}), is determined, in that at least one threshold value is selected, and in that the pressure gradient or a variable derived from the pressure gradient is compared with the at least one threshold value and, if the threshold value is overshot or undershot, a signal is generated.

Abstract: The disclosure relates to a method for operating a gas turbine plant which is supplied with a fuel gas via a compressor station. The compressor station includes a compressor which compresses the fuel gas which is fed via a gas feed line and delivers it via at least one control valve to a combustion chamber of the gas turbine plant. A bypass system is arranged in parallel to the compressor via which fuel gas can be directed in a switchable manner past the compressor to the at least one control valve. An energy-saving operation can be achieved in a simple manner by continuously measuring the fuel gas pressure at the outlet of the at least one control valve. A minimum fuel gas pressure, which is desired (e.g., necessary) for operation of the gas turbine, at the inlet of the at least one control valve is determined from the measured pressure values in each case.

Abstract: A method for protecting a gas turbine installation from overheating and for detecting flame extinction in the combustion chamber is described, in which air is compressed in a compressor unit and, after being admixed with fuel, is ignited in the form of a fuel/air mixture in a combustion chamber and is burnt, thus giving rise to a hot gas flow which sets a turbine stage in rotation downstream of the combustion chamber so as to perform expansion work. The pressure upstream of the turbine stage, that is to say the pressure pk of the compressed air in the plenum and/or the pressure within the combustion chamber pcom, is measured, in that a time change of the measured pressure, what is known as the pressure gradient ({dot over (p)}), is determined, in that at least one threshold value is selected, and in that the pressure gradient or a variable derived from the pressure gradient is compared with the at least one threshold value and, if the threshold value is overshot or undershot, a signal is generated.