PARTIAL-LOAD OPERATION OF A GAS TURBINE WITH AN ADJUSTABLE BYPASS FLOW CHANNEL

A gas turbine has a compressor providing compressed air, a combustion chamber provided with a burner, and an expansion turbine, wherein a bypass flow channel is also provided designed to supply compressed air past the burner and to supply a hot gas flow generated in the combustion chamber during ope...

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Bibliographische Detailangaben
Hauptverfasser:	Kleinenhammann Matthias, Knüwer Norbert, Engler Thorsten, Wagner Ulrich, Tertilt Marc, Kerstiens Thomas, Süselbeck Kai, Gutermuth Manuel, Weidner Frank
Format:	Patent
Sprache:	eng
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS ENGINE PLANTS IN GENERAL GAS-TURBINE PLANTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES NON-POSITIVE DISPLACEMENT PUMPS POSITIVE DISPLACEMENT MACHINES FOR LIQUIDS PUMPS FOR LIQUIDS OR ELASTIC FLUIDS STEAM ENGINES WEAPONS
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Beschreibung
Zusammenfassung:	A gas turbine has a compressor providing compressed air, a combustion chamber provided with a burner, and an expansion turbine, wherein a bypass flow channel is also provided designed to supply compressed air past the burner and to supply a hot gas flow generated in the combustion chamber during operation of the gas turbine. The opening cross section of the bypass flow channel can be adjusted, and an adjustment unit is designed to adjust the opening cross section of the bypass flow channel such that the modification speed of the opening cross section is selected such that the relative combustion chamber pressure drop or a material temperature of the combustion chamber is substantially constant, in particular that the relative combustion chamber pressure drop or the material temperature of the combustion chamber does not vary by more than 10%.