Alstom Technology Limited

Ansaldo Energia IP UK Limited

Ansaldo Energia Switzerland Ag

Mengbin Zhang

Adnan Eroglu

Stefano Bernero

Weiqun Geng

Klaus-Dieter Liedtke

Aysegul Kirecci

Ulf Schirmeister

Martin Erwin Gassner

Sebastian Lipari

Tobias Spitzmueller

Norbert Walter Emberger

Wenceslao Granados Gomez

Andreas Jan Schesny

Tobias Spitzmüller

Manuel Ramirez-Espana-Mejia

Pankaj Bajaj

Michael Kenyon

Frank Keppler

Tobias Christian Amsler

Zlatko Pavlic

Dirk Therkorn

Martin Gassner

Vincent Lonneux

Frank Keppeler

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.

Method for controlling the operation of a gas turbine with an averaged turbine outlet temperature

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.

Gas turbine having fuel monitoring

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

Method for operating a gas turbine and gas turbine unit useful for carrying out the method

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 (s) is generated based on a fuel mass flow control command (m) using a mass flow-valve stroke converter. The valve stroke control command (s) is compared with a valve stroke limit value (min{s, s}) using a variable pressure regulator. A load limit value is generated if the valve stroke control command (s) exceeds the valve stroke limit value (min{s, s}) to reduce the load setpoint value. Operation of the gas turbine is stabilized using a low limit value (x) 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 (p) upstream of the control valve.

Method for operating a gas turbine

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. The compressor station can be switched over to bypass operation when the fuel gas pressure which reaches the inlet of the at least one control valve via the bypass system is greater than or equal to the minimum fuel gas pressure.

Method for operating a gas turbine plant with a compressor station for gaseous fuel

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 pof the compressed air in the plenum and/or the pressure within the combustion chamber p, 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.

Method for protecting the hot gas parts of a gas turbine installation from overheating and for detecting flame extinction in the combustion chamber

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Otelfingen, Switzerland

Mengbin Zhang