초록 ▼

The invention relates to a gas turbine (3) with reheat in the turbine section (11), whereby a fuel injection device (37) is provided for the injection of fuel (33) in to a combustion air flow (61) in the direction of flow before a cooling air flow (65) branching. By means of the early mixing of fuel

The invention relates to a gas turbine (3) with reheat in the turbine section (11), whereby a fuel injection device (37) is provided for the injection of fuel (33) in to a combustion air flow (61) in the direction of flow before a cooling air flow (65) branching. By means of the early mixing of fuel (63) in the combustion air flow (61) and concomitant additional use of the cooling air flow (65) as combustion air, the specific output and the efficiency of the gas turbine (3) are improved.

대표청구항 ▼

1. A gas turbine, comprising:a compressor for generating a compressed combustion air flow which flows along a flow direction; a hot-gas region, including a combustion chamber and a turbine part with a hot gas flow duct; and a cooling air supply system for branching off a cooling air flow from the co

1. A gas turbine, comprising:a compressor for generating a compressed combustion air flow which flows along a flow direction; a hot-gas region, including a combustion chamber and a turbine part with a hot gas flow duct; and a cooling air supply system for branching off a cooling air flow from the combustion air flow at a branch position and supplying it to a thermally stressed hot gas component of the hot gas region; wherein a fuel supply device is provided for the supply of fuel to the combustion air flow at a fuel supply position; wherein the fuel supply position is arranged, viewed in the flow direction, before the branch position; wherein the fuel and the cooling air flow are branched directly adjacent a pilot burner into at least two cooling passages inclusive of a first cooling passage and a second cooling passage, the first cooling passage delivering fuel and cooling air flow to the hot gas component; and wherein the cooling air supply system directs at least a portion of the cooling air flow mixed with fuel from the fuel supply device along an inner lining of the combustion chamber via the second cooling passage, through openings in the inner lining, and into the combustion chamber in which the cooling air flow mixed with fuel self-ignites. 2. The gas turbine as claimed in claim 1, wherein the fuel supply device is designed in such a way that at least 80% of a fuel mass flow being burnt in total per unit time is suppliable via the fuel supply device.3. The gas turbine as claimed in claim 2, wherein the fuel supply device is connected to a fuel reservoir for a gaseous fuel.4. The gas turbine as claimed in claim 2, wherein the hot gas component is a turbine blade/vane.5. The gas turbine as claimed in claim 1, wherein the fuel supply device is connected to a fuel reservoir for a gaseous fuel.6. The gas turbine as claimed in claim 5, wherein the hot gas component is a turbine blade/vane.7. The gas turbine as claimed in claim 1, wherein the hot gas component is a turbine blade/vane.8. The gas turbine as claimed in claim 7, wherein the hot gas component is a guide vane.9. The gas turbine as claimed in claim 8, wherein the hot gas component is a guide vane of a first guide vane row, viewed in flow direction, in the hot gas flow duct.10. The gas turbine as claimed in claim 8, wherein the hot gas component is a rotor blade of a first rotor blade row, viewed in flow direction, in the hot gas flow duct.11. The gas turbine as claimed in claim 1, wherein the inner lining of the combustion chamber has a wall segment.12. The gas turbine as claimed in claim 1, wherein the fuel supply position is located in the compressor.13. The gas turbine as claimed in claim 12, wherein the fuel supply device comprises a compressor guide vane.14. The gas turbine as claimed in claim 13, wherein the compressor guide vane is part of a last compressor guide vane row, viewed in flow direction.15. The gas turbine as claimed in claim 1, wherein the fuel supply device is connected to a fuel reservoir for methane.16. A method for operating a gas turbine having a compressor and a hot gas region, comprising a combustion chamber and a turbine part with a hot gas flow duct, the method comprising:generating a compressed combustion air flow flowing along a flow direction, in the compressor; supplying fuel to the combustion air flow at a fuel supply position to produce a combustion air/fuel mixture; branching a cooling air flow off from the combustion air/fuel mixture; and supplying the cooling air flow to a thermally highly stressed hot gas component arranged in the hot gas region; wherein the fuel and the cooling air flow are branched directly adjacent a pilot burner into at least two cooling passages inclusive of a first cooling passage and a second cooling passage, the first cooling passage delivering fuel and cooling air flow to the hot gas component; and wherein at least a portion of the cooling air flow is supplied along an inner lining of the combustion chamber via the second cooling passage, through openings in the inner lining, and into the combustion chamber in which the cooling air flow self-ignites. 17. The method as claimed in claim 16, wherein methane is used as the fuel.18. The method as claimed in claim 16, wherein long-chain hydrocarbons are admixed to the fuel.19. The method as claimed in claim 16, wherein a guide vane of a first guide vane row, viewed in flow direction, of the turbine part is cooled by the cooling air flow.20. The method as claimed in claim 16, wherein a rotor blade of a first rotor blade row, viewed in flow direction, of the turbine part is cooled by the cooling air flow.21. The method as claimed in claim 16, wherein the supply of the fuel to the combustion air flow takes place via a compressor guide vane.22. The method as claimed in claim 21, wherein the supply of the fuel to the combustion air flow takes via a compressor guide vane of a last guide vane row, viewed in flow direction, of the compressor.23. The method as claimed in claim 16, wherein at least 80% of a fuel mass flow being burnt, in total, per unit time is supplied to the combustion air flow at the fuel supply position.24. A gas turbine, comprising:compressor means for generating a compressed combustion air flow which flows along a flow direction; a hot-gas region, including a combustion chamber and a turbine part with a hot gas flow duct; cooling air supply means for branching off a cooling air flow from the combustion air flow at a branch position and supplying it to a thermally stressed hot gas component of the hot gas region; and fuel supply means for the supply of fuel to the combustion air flow at a fuel supply position; wherein the fuel supply position is arranged, viewed in the flow direction, before the branch position; wherein the fuel and the cooling air flow are branched directly adjacent a pilot burner into it least two cooling passages inclusive of a first cooling passage and a second cooling passage, the first cooling passage delivering fuel and cooling air flow to the hot gas component; and wherein the cooling air supply means directs at least a portion of the cooling air flow mixed with fuel from the fuel supply means along an inner lining of the combustion chamber via the second cooling passage, through openings in the inner lining, and into the combustion chamber in which the cooling air flow mixed with fuel self-ignites. 25. The gas turbine as claimed in claim 24, wherein the fuel supply means is designed in such a way that at least 80% of a fuel mass flow being burnt in total per unit time is suppliable via the fuel supply device.26. The gas turbine as claimed in claim 24, wherein the fuel supply means is connected to a fuel reservoir for a gaseous fuel.27. The gas turbine as claimed in claim 24, wherein the hot gas component is a turbine blade/vane.28. The gas turbine as claimed in claim 24, wherein the hot gas component is a guide vane.29. The gas turbine as claimed in claim 28, wherein the hot gas component is a guide vane of a first guide vane row, viewed in flow direction, in the hot gas flow duct.30. The gas turbine as claimed in claim 27, wherein the hot gas component is a rotor blade of a first rotor blade row, viewed in flow direction, in the hot gas flow duct.