Abstract: A method for operating a stationary gas turbine at partial load, having at least one compressor, at least one expansion turbine and a combustion chamber provided with at least one burner, which gas turbine further includes a hydraulic gap adjuster, wherein the method has the following steps: operating the gas turbine at partial load; operating the a hydraulic gap adjuster; during the operation of the hydraulic gap adjuster, increasing the fuel supply to the burner while increasing the temperature of the combustion gases which are guided to the expansion turbine.

Abstract: 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.

Abstract: A method for regulating a gas turbine wherein the fuel quantity supplied to the burners of the gas turbine is regulated using a target value for the corrected turbine outlet temperature. A stable operation of the gas turbine is to be allowed with a particularly high degree of efficiency and a high output at the same time. The target value for the corrected turbine outlet temperature is set using a value which characterizes the combustion stability in the burners, wherein the target value for the corrected turbine outlet temperature is set additionally using the surrounding temperature. Furthermore, the target value for the corrected turbine outlet temperature is set only below a specified surrounding temperature using the value which characterizes the combustion stability in the burners.

Abstract: A gas turbine having an axially adjustable rotor, has the following components: at least one external compressor air bleed for bleeding compressor air; a control valve for adjusting the amount of compressor air bled via the at least one external compressor air bleed; an axial thrust piston that can be supplied with the compressor bleed air via a supply line in such a way that a different axial compensation thrust is applied to same when the amount of compressor bleed air is adjusted; and a radial bearing which cooperates with the axial thrust piston for bearing purposes, and which can also be directly or indirectly supplied with the compressor bleed air via the supply line.

Abstract: A gas turbine having a wet compression device which allows droplets of an aqueous liquid mixture to be introduced into a compressor of the gas turbine during operation of the gas turbine, the aqueous liquid mixture containing at least one surfactant. The aqueous liquid mixture additionally contains at least a defoaming agent, and the gas turbine has a second metering device, which is designed to feed a predetermined quantity of defoaming agent into water which is provided for use in the wet compression device.

Abstract: 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.

Abstract: A method for operating a stationary gas turbine at partial load, having at least one compressor, at least one expansion turbine and a combustion chamber provided with at least one burner, which gas turbine further includes a hydraulic gap adjuster, wherein the method has the following steps: operating the gas turbine at partial load; operating the a hydraulic gap adjuster; during the operation of the hydraulic gap adjuster, increasing the fuel supply to the burner while increasing the temperature of the combustion gases which are guided to the expansion turbine.

Abstract: A method for operating a gas turbine system in part load operation wherein a compressor pre-guide blade adjustment for part load operation is initiated in case of a given state of a flow medium which flows into a compressor, a value of the initiated compressor pre-guide blade adjustment is compared with a compressor pre-guide blade adjustment limit value which is determined depending on the state of the flow medium, and, if the value of the initiated compressor pre-guide blade adjustment meets a predefined condition with regard to the compressor pre-guide blade adjustment limit value, at least one measure is initiated for changing the state of the flow medium which flows into the compressor in part load operation. An arrangement has an actuating device, determining device and control unit to carry out the method. The gas turbine system has an anti-icing device and/or an intake air heating device and the arrangement.

Abstract: A method for regulating a gas turbine wherein the fuel quantity supplied to the burners of the gas turbine is regulated using a target value for the corrected turbine outlet temperature. A stable operation of the gas turbine is to be allowed with a particularly high degree of efficiency and a high output at the same time. The target value for the corrected turbine outlet temperature is set using a value which characterizes the combustion stability in the burners, wherein the target value for the corrected turbine outlet temperature is set additionally using the surrounding temperature. Furthermore, the target value for the corrected turbine outlet temperature is set only below a specified surrounding temperature using the value which characterizes the combustion stability in the burners.

Abstract: A method for reducing the CO emissions of a gas turbine having a compressor, a turbine and an air preheater positioned upstream of the compressor, that permits technically simpler regulation without losses in terms of the quality of the reduction of the CO emissions. The heat transfer power of the air preheater is regulated on the basis of a minimum value for the inlet temperature of the compressor, wherein the minimum value is predefined as a function of the absolute power of the gas turbine.

Abstract: 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.

Abstract: 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.

Abstract: A heat-shield element (14), for lining a combustion-chamber wall (13), the chamber wall has a first wall (17) with a hot side (18) which can be loaded with a hot medium, a cold side (19) which lies opposite the hot side (18), and a circumferential edge (24) which extends on a first (20), a second (21) and a third narrow side (22) of the first wall (17) to a first height (25) beyond the cold side (19), the circumferential edge (24) extends on a fourth narrow side (23) to a second shorter height (26), substantially at the second height (26), a second wall (27) lies opposite the cold side (19) and extends over the width of the fourth narrow side (23) from the fourth narrow side (23) and over a part of the length of the narrow sides (20, 22), which adjoin the fourth narrow side; (23), the second wall (27) has an edge (29) at the end (28) thereof which faces away from the fourth narrow side (23), which edge (29) extends to the first height (25). Furthermore, a combustion chamber and a gas turbine are disclosed.

Abstract: An annular combustion chamber (1) for a gas turbine, the chamber having an outer shell (12) which has at least one inlet opening (4) for a burner (3) and an outlet (7) which opens into a turbine chamber (8), wherein ducts (14) which can be closed, which are oriented substantially parallel to the symmetry axis (2) of the annular combustion chamber (1), and through which final compressor air is guided into the annular combustion chamber (1) are provided in the outer shell (12) in the region of the outlet (7). Ring segments around the outer shell have projections selectively movable to at least partially block and open the ducts. A gas turbine is also disclosed.

Abstract: A stator blade carrier for a gas turbine is provided. The stator blade carrier includes a plurality of axial segments. At least one axial segment is designed as a tubular lattice structure. This allows a simpler design technically and a more flexible adaptation to the temperature profile present on the stator blade carrier to maintain operational safety.

Abstract: A turbomachine rotor, a rotor blade and a method for assembling a turbomachine rotor are provided. The turbomachine rotor includes a rotor blade with a blade root, a wheel disk with a groove in which the blade root engages such that the rotor blade is maintained in the groove in a positive fit in a radial direction. Further, a pretensioning device is provided, which is supported on the wheel disk as well as on the blade root and which exerts a pretensioning force on the blade root in the radial direction. The pretensioning device is designed such that the pretensioning force can be adjusted when assembling the turbomachine rotor.

Abstract: A fastening assembly for blades of turbomachines through which axial flow can take place, preferably compressors, includes a blade carrier having a lateral face, in which retaining groves are distributed along the circumference, with blades being inserted in the grooves, wherein a resilient tensioning element is provided between each groove base and the underside of the respective blade foot, the underside being located opposite of the groove base. The tensioning element is supported on the respective underside and on the respective groove base in a pretensioning manner, wherein a channel is provided both in the groove base and in the underside, with the tensioning element resting in the channels.

Abstract: A rotor blade system, for example, of a gas turbine is provided. The rotor blade system includes a plurality of rotor blades which are arranged annularly on a rotor disk. A plurality of sealing plates are arranged on a side surface of the rotor disk. An individual sealing plate is formed from a plurality of metal sheets, wherein two of the metal sheets are arranged opposite each other a distance apart and parallel to a plane of the sealing plate, forming a gap for guiding of cooling air.

Abstract: A stator blade carrier for a gas turbine is provided. The stator blade carrier includes a plurality of axial segments. At least one axial segment is designed as a tubular lattice structure. This allows a simpler design technically and a more flexible adaptation to the temperature profile present on the stator blade carrier to maintain operational safety.

Abstract: A turbomachine rotor, a rotor blade and a method for assembling a turbomachine rotor are provided. The turbomachine rotor includes a rotor blade with a blade root, a wheel disk with a groove in which the blade root engages such that the rotor blade is maintained in the groove in a positive fit in a radial direction. Further, a pretensioning device is provided, which is supported on the wheel disk as well as on the blade root and which exerts a pretensioning force on the blade root in the radial direction. The pretensioning device is designed such that the pretensioning force can be adjusted when assembling the turbomachine rotor.