Siemens Aktiengesellschaft

Markus Gorynski

Thorsten Engler

Marc Tertilt

Nicolas Savilius

Marco Link

Philipp Kreutzer

Manuel Gutermuth

Kai Suselbeck

Ansgar Sternemann

Rebecca Dierkes

Kai Süselbeck

Kai SÜSELBECK

A method for operating a gas turbine plant having a compressor and a turbine, where a limit value of a guide blade adjustment for the compressor of the gas turbine is identified depending on at least one drive shaft speed of the gas turbine plant. For the at least one drive shaft speed, a maximum allowable turbine entry temperature corresponding to the limit value of the guide vane adjustment for the compressor or a maximum allowable temperature for the turbine of the gas turbine, which is dependent on the turbine entry temperature, is identified. The gas turbine is operated in consideration of the identified maximum allowable turbine entry temperature or the identified maximum allowable temperature.

Operation of a gas turbine plant having a compressor and a turbine

A method for operating a gas turbine below the nominal power includes: determining a lower power threshold value of the gas turbine which causes the gas turbine to leave a CO-emission-compliant partial load range of the gas turbine; providing a specified threshold value for output gas turbine power, wherein the specified threshold value is less than the nominal power of the gas turbine; and operating the gas turbine at an output gas turbine power above the specified threshold value at a constant exhaust gas temperature, wherein the inlet guide blades of a compressor of the gas turbine are closed further in order to reduce the output gas turbine power. A sufficiently large valve is selected for the specified threshold value so that increases of the primary zone temperature, combustion temperature, and exhaust temperature extend over a CO-emission-compliant partial load range of the gas turbine that is as large as possible.

Method for operating a gas turbine below the nominal power thereof

A gas turbine includes an intake tract and a compressor having a compressor flow channel. The compressor further includes an inlet guide vane row positioned in the compressor flow channel having inlet guide vanes that can be adjusted. The gas turbine has an icing sensor unit having at least one sensor arranged between a first compressor blade row and a first compressor guide vane row. The first compressor blade row is thereby arranged in the compressor flow channel directly downstream of the inlet guide vane row, and the first compressor guide vane row is arranged directly downstream of the first compressor blade row. A method detects an imminent icing of the compressor, and the compressor is safeguarded therefrom such that at least inlet guide vanes of the inlet guide vane row are adjusted such that the acceleration of an intake air mass flow is reduced.

Gas turbine and method for operating the gas turbine

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Bochum, Germany

Markus Gorynski