초록 ▼

The invention concerns a gas turbine combustion system, including a gas turbine. The gas turbine includes at least one compressor, at least one combustion chamber for generating working gas, wherein the combustion chamber connected to receive compressed air from the compressor, at least one turbine

The invention concerns a gas turbine combustion system, including a gas turbine. The gas turbine includes at least one compressor, at least one combustion chamber for generating working gas, wherein the combustion chamber connected to receive compressed air from the compressor, at least one turbine connected to receive working gas from the combustion chamber. The combustion chamber consists of an individual can-combustor or comprising a number of can-combustors arranged in an annular can-architecture, wherein the can-combustor having at least one premixed burner. The ignition of the mixture starts at the premixed burner outlet and the flame is stabilized in the region of the premixed burner outlet by means of a backflow zone. The can-combustor comprising a number of premixed burners arranged uniformly or divided at least in two groups within the can-combustor.

대표청구항 ▼

1. A gas turbine combustion system including a gas turbine, wherein the gas turbine comprises: at least one compressor;at least one combustion chamber for generating working gas, wherein the at least one combustion chamber is connected to receive compressed air from the at least one compressor; anda

1. A gas turbine combustion system including a gas turbine, wherein the gas turbine comprises: at least one compressor;at least one combustion chamber for generating working gas, wherein the at least one combustion chamber is connected to receive compressed air from the at least one compressor; andat least one turbine connected to receive working gas from the at least one combustion chamber,wherein the at least one combustion chamber includes at least two can-combustors arranged in an annular can-architecture,wherein each can-combustor includes a plurality of premixed burners, wherein the plurality of premixed burners of each can-combustor is divided in two groups, each with one or more premixed burners, wherein a first group is positioned in a can-combustor face and a second group is positioned downstream of the first group in an axial position, wherein one or more premixed burners of the second group is axially aligned in an oblique position with respect to an axial extension of each can-combustor; andwherein ignition of a mixture of air and fuel starts at each premixed burner outlet of the second group and a flame is stabilized in a region of the outlet of each premixed burner of the second group by a backflow zone. 2. The gas turbine combustion system according to claim 1, wherein each of the plurality of premixed burners comprises a swirl generator that includes hollow part-cone bodies making up a complete body, having tangential air inlet slots and feed channels for gaseous and liquid fuels, wherein center axes of the hollow part-cone bodies have a cone angle increasing in a direction of flow and run in a longitudinal direction at a mutual offset, wherein a fuel nozzle, which fuel injection is located in a middle of a connecting line of mutually offset center axes of the hollow part-cone bodies, is placed at a burner head in a conical interior formed by the hollow part-cone bodies, and a mixing tube provided downstream of said swirl generator, wherein said mixing tube comprises transition ducts extending within a first part of a path in a flow direction for transfer of a flow formed in said swirl generator into a cross-section of flow of said mixing tube, that joins downstream of said transition ducts. 3. The gas turbine combustion system according to claim 2, wherein the mixing tube is shaped with variable diameter and/or length along an axis of a respective pre-mixed burner. 4. The gas turbine combustion system according to claim 2 wherein each premixed burner comprises a premixed, or partially pre-mixed or non-premixed pilot nozzle for ignition and reduction of a lean blow off temperature at part-load operation. 5. The gas turbine combustion system according to claim 4 wherein the premixed, or partially pre-mixed or non-premixed pilot nozzle is arranged at one of said one or more premixed burners' exit, or on a fuel lance of the swirl generator, or is placed in-between a plurality of premixed burners. 6. The gas turbine combustion system according to claim 2 wherein low frequency dynamics of each can-combustor is controlled by a Helmholtz damper, wherein the Helmholtz damper is a freestanding cylindrical Helmholtz cavity and neck, or a Helmholtz cavity in a free space between the mixing tubes of the premixed burner. 7. The gas turbine combustion system according to claim 6, wherein each Helmholtz damper is divided into segments to prevent low frequency pressure oscillations. 8. The gas turbine combustion system according to claim 2 wherein distribution of compressed air from the at least one compressor to each premixed burner is supported by sieves or a strainer positioned around of the swirl generators. 9. The gas turbine combustion system according to claim 1 wherein said can-combustor face of each can-combustor is designed as an acoustic damper for damping of high frequency acoustic pressure oscillations. 10. A gas turbine combustion system, including a gas turbine, wherein the gas turbine comprises: at least one compressor;a first combustion chamber for generating working gas, wherein the first combustion chamber is connected to receive compressed air from the at least one compressor, andwherein hot gases of the first combustion chamber are admitted at least to an intermediate turbine or directly or indirectly to a second combustion chamber, andwherein hot gases of the second combustion chamber are admitted to a further turbine or directly or indirectly to an energy recovery, andwherein the first and/or the second combustion chamber includes at least two can-combustors arranged in an annular can-architecture,each can-combustor including a plurality of premixed burners, wherein ignition of a mixture of air and fuel starts at a premixed burner outlet and a flame is stabilized in a region of each premixed burner outlet by a backflow zone, wherein the plurality of premixed burners of each can-combustor is divided in two groups, each with one or more premixed burners, wherein a first group is positioned in a can-combustor face and a second group is positioned downstream of the first group in an axial position, wherein one or more premixed burners of the second group is axially aligned in an oblique position with respect to an axial extension of each can-combustor. 11. The gas turbine combustion system according to claim 10, wherein each premixed burner comprises a swirl generator, each swirl generator includes hollow part-cone bodies making up a complete body, having tangential air inlet slots and feed channels for gaseous and/or liquid fuels, wherein center axes of the hollow part-cone bodies have a cone angle increasing in a direction of flow and run in a longitudinal direction at a mutual offset, wherein a fuel nozzle, which fuel injection is located in a middle of a connecting line of mutually offset center axes of the hollow part-cone bodies, is placed at a burner head in a conical interior formed by the hollow part-cone bodies.