Abstract: The invention relates to a premix burner of the multi-cone type for a gas turbine that includes a plurality of shells which are arranged around a central burner axis and are parts of a virtual, axially extending common cone, which opens in a downstream direction, whereby said parts are displaced perpendicular to said burner axis such that a tangential slot is defined between each pair of adjacent shells. The flame front of such a burner is stabilized by providing a virtual common cone with a cone angle, which varies in axial direction.

Abstract: In method for operating a gas turbine (11), the compressed air is fed to a combustor (18, 19) for the combustion of a coal syngas, and the resulting hot gases are expanded in a subsequent turbine (16, 17). Some of the compressed air is separated into oxygen and nitrogen, and the oxygen is used for producing the syngas. In a first combustor, (18) syngas is combusted and the resulting hot gases are expanded in a first turbine (16), and in a second combustor syngas is combusted, using the gases which issue from the first turbine (16), and the resulting hot gases are expanded in the second turbine (17). The two combustors (18, 19) are operated with undiluted syngas, and the first combustor flame temperature (TF) is lowered compared with the operation with natural gas (TNG), while the second combustor (19) is operated in the normal operation (TNG) for natural gas.

Abstract: A method is disclosed for operating a gas turbine power plant having a gas turbine, a heat recovery steam generator and an flue gas splitter which splits flue gases into a first flue gas flow for recirculation into an inlet flow of the gas turbine and into a second flue gas flow for discharge to an environment. An oxygen-depleted gas can be used in an open cooling system for cooling hot gas parts of the gas turbine. A split compressor intake can be provided for separate feed of recirculated flue gas and fresh air into a compressor intake. Compressor blades can include a separating band which blocks intermixing of recirculated flue gas and fresh air during compression.

Abstract: In a method for adjusting a Helmholtz resonator (10), in which a resonator volume (11) is connected to a space (13) to be provided with damping along an axis (29) via a constriction (12) having an acoustic impedance, the acoustic impedance of the constriction (12) is altered in order to adjust the Helmholtz resonator (10).

Abstract: A burner (1) for a combustion chamber of a turbogroup includes a swirl generator (2), a mixer (3), and a lance (4) for introducing pilot fuel into a combustion space (10). In order to stabilize combustion, the lance (4) is designed and/or arranged so that, at least in the pilot mode of the burner (1), it extends far enough into the burner interior (5) for a flame front (16) of a combustion reaction, which takes place in the combustion space (10), to extend at least partially into the burner interior (5).

Abstract: An exemplary method for the operation of a CCPP with flue gas recirculation to reduce NOx emissions and/or to increase the CO2 concentration in the flue gases to facilitate CO2 capture from the flue gases as well as a plant designed to operate is disclosed. To allow a high flue gas recirculation ration (rFRG) an imposed combustion inhomogeneity ratio (ri) is used for flame stabilization. The imposed combustion inhomogeneity ratio (ri) is controlled as function of the flue gas recirculation rate (rFRG) and/or combustion pressure. Oxygen or oxygen enriched air to the gas turbine inlet gases or to the combustor is admixed to enhance operatability.

Abstract: An exemplary system method for the operation of a CCP P with flue gas recirculation to reduce NOx emissions and/or to increase the CO2 concentration in the flue gases to facilitate CO2 capture from the flue gases is disclosed. The flue gas recirculation rate (rFRG) is controlled as function of the combustion pressure and/or the hot gas temperature. Operability is enhanced by admixing of oxygen or oxygen enriched air to the gas turbine inlet gases or to the combustion.

Abstract: In a method for adjusting a Helmholtz resonator (10), in which a resonator volume (11) is connected to a space (13) to be provided with damping along an axis (29) via a constriction (12) having an acoustic impedance, the acoustic impedance of the constriction (12) is altered in order to adjust the Helmholtz resonator (10).

Abstract: In a method for operating a gas turbine (GT) with sequential combustion, which has at least one compressor (12, 13), a first combustion chamber (14) with a first turbine (15) which is connected downstream, and a second combustion chamber (16) with a second turbine (17) which is connected downstream, the at least one compressor (12, 13) draws in air and compresses it. The compressed air is fed to the first combustion chamber (14) for combusting a first fuel, and the gas which issues from the first turbine (15) is fed to the second combustion chamber (16) for combusting a second fuel. Increased flexibility and safety in operation is achieved by different fuels being used as first and second fuel.

Abstract: A burner (1) for a combustion chamber of a turbogroup includes a swirl generator (2), a mixer (3), and a lance (4) for introducing pilot fuel into a combustion space (10). In order to stabilize combustion, the lance (4) is designed and/or arranged so that, at least in the pilot mode of the burner (1), it extends far enough into the burner interior (5) for a flame front (16) of a combustion reaction, which takes place in the combustion space (10), to extend at least partially into the burner interior (5).

Abstract: A method for operating a gas turbine (11), which is used especially in a combined-cycle power plant (30), includes inducting and compressing air by the gas turbine (11), the compressed air is fed to a combustor (18, 19) for the combustion of a syngas which is produced from coal, and the hot gases which result during the combustion are expanded in a subsequent turbine (16, 17), performing work, wherein some of the compressed air is separated into oxygen and nitrogen, and the oxygen is used in a coal gasification plant (34) for producing the syngas.

Abstract: In a method for operating a gas turbine (11) in a combined cycle power plant (40), air is drawn in and compressed though the gas turbine (11), the compressed air is led to a combustor (18, 19) to burn a syngas recovered from a fossil fuel, especially coal, and the gases that result in the course of the combustion are expanded in a downstream turbine (16, 17). In such a method, an improved degree of efficiency is achieved by virtue of the fact that a gas turbine (11) with reheating is used, which includes two combustors (18, 19) and two turbines (16, 17); in the first combustor (18), syngas is burned with the compressed air, and the resultant hot gases, e.g., flue gases, are expanded in the first turbine (16), and in the second combustor syngas is burned by the gases coming from the first turbine (16), and the resultant hot gases are expanded in the second turbine (17).

Abstract: In a method for operating a gas turbine (GT) with sequential combustion, which has at least one compressor (12, 13), a first combustion chamber (14) with a first turbine (15) which is connected downstream, and a second combustion chamber (16) with a second turbine (17) which is connected downstream, the at least one compressor (12, 13) draws in air and compresses it. The compressed air is fed to the first combustion chamber (14) for combusting a first fuel, and the gas which issues from the first turbine (15) is fed to the second combustion chamber (16) for combusting a second fuel. Increased flexibility and safety in operation is achieved by different fuels being used as first and second fuel.

Abstract: A method for operating a gas turbine (2), in particular in a power plant, includes operating the gas turbine (2) with natural gas. In order to adapt the gas turbine operation to different natural gas qualities, a concentration of C2+ is measured in the natural gas during gas turbine (2) operation. The gas turbine (2) then is operated based on the current concentration of C2+.

Abstract: A premix burner is disclosed, with a swirl generator which delimits a conical swirl space and provides at least two conical part shells which are arranged, offset to one another, along a burner axis, mutually enclose in each case air inlet slits running longitudinally with respect to the burner axis and have in combination a conically widening premix burner outer contour having a maximum outside diameter which narrows axially into a region with a minimum outside diameter. At least one conical part shell provides, in the region between the maximum and the minimum outside diameter, a reception unit which deviates from the conically widening premix burner outer contour and locally elevates the premix burner outer contour radially outward and which has a maximum radial extent which is dimensioned smaller than half the maximum outside diameter of the premix burner outer contour.

Abstract: A premix burner is disclosed, with a swirl generator which delimits a conical swirl space and provides at least two conical part shells which are arranged, offset to one another, along a burner axis, mutually enclose in each case air inlet slits running longitudinally with respect to the burner axis and have in combination a conically widening premix burner outer contour having a maximum outside diameter which narrows axially into a region with a minimum outside diameter. At least one conical part shell provides, in the region between the maximum and the minimum outside diameter, a reception unit which deviates from the conically widening premix burner outer contour and locally elevates the premix burner outer contour radially outward and which has a maximum radial extent which is dimensioned smaller than half the maximum outside diameter of the premix burner outer contour.

Abstract: In a method for operating a gas turbine (11) in a combined cycle power plant (40) air is drawn in and compressed through the gas turbine (11), the compressed air is led to a combustor (18, 19) to burn a syngas recovered from a fossil fuel, especially coal, and the gases that result in the course of the combustion are expanded in a downstream turbine (16, 17). In such a method, an improved degree of efficiency is achieved by virtue of the fact that a gas turbine (11) with reheating is used, which includes two combustors (18, 19) and two turbines (16, 17), whereby in the first combustor (18), syngas is burned with the compressed air, and the resultant hot gases, e.g., flue gases, are expanded in the first turbine (16), and whereby in the second combustor syngas is burned by means of the gases coming from the first turbine (16) and the resultant hot gases are expanded in the second turbine (17).

Abstract: A description is given of a damping arrangement for reducing resonant vibrations in a combustion chamber (1), with a combustion-chamber wall (2), which is of double-walled design and, with an outer wall-surface part (22) and an inner wall-surface part (21) facing the combustion chamber (1), gastightly encloses an intermediate space (3), into which cooling air can be fed for purposes of convective cooling of the combustion-chamber wall (2). The invention is distinguished by the fact that at least one third wall-surface part (4) is provided, which, with the outer wall-surface part (22), encloses a gastight volume (5), and that the gastight volume (5) is connected gastightly to the combustion chamber (1) by at least one connecting line (6).

Abstract: A method for operating a gas turbine (2), in particular in a power plant, includes operating the gas turbine (2) with natural gas. In order to adapt the gas turbine operation to different natural gas qualities, a concentration of C2+ is measured in the natural gas during gas turbine (2) operation. The gas turbine (2) then is operated based on the current concentration of C2+.

Abstract: A gas turbo group has a combustion chamber comprising a catalytic burner stage (2), a preburner stage (1) located upstream from the catalytic burner stage, as well as a non-catalytic burner stage (11, 5, 6) located downstream from the catalytic burner stage. The preburner stage serves to always maintain a temperature (T1) at the inlet into the catalytic stage that corresponds at least to a minimum temperature (TMIN) necessary for operating the catalytic burner stage. According to the invention, the gas turbo group is operated so that the burner stage located downstream from the catalytic combustion chamber is taken into operation only when the temperature (T2) at the outlet from the catalytic stage has reached an upper limit in the presence of a maximum combustion air mass flow.