A premix burner includes a swirler (7) for a combustion air stream and a device for injection of fuel into the combustion air stream. The swirler (7) includes one or more inlet openings for combustion air of the combustion air stream entering the burner. The device for injection of fuel into the co
A premix burner includes a swirler (7) for a combustion air stream and a device for injection of fuel into the combustion air stream. The swirler (7) includes one or more inlet openings for combustion air of the combustion air stream entering the burner. The device for injection of fuel into the combustion air stream includes one or more first fuel lines (8) with first fuel injection openings (4). The opening diameter and/or the injection angle of the injection openings varies with respect to the axial and/or radial direction. Alternatively or in addition, some of the first fuel injection openings (4) may be arranged in one or more first groups of closely grouped fuel injection openings (4) so that each of the first groups forms one fuel jet with a large cross section. An improved mixing of the fuel with the combustion air is achieved with the burner in particular in cases in which the fuel is injected at the end of the burner facing the combustion chamber.
대표청구항▼
What is claimed is: 1. A premix burner comprising: a central longitudinal axis defining an axial direction, and a radial direction oriented towards the central longitudinal direction; a swirler for a combustion air stream, the swirler at least one combustion air inlet opening for the combustion ai
What is claimed is: 1. A premix burner comprising: a central longitudinal axis defining an axial direction, and a radial direction oriented towards the central longitudinal direction; a swirler for a combustion air stream, the swirler at least one combustion air inlet opening for the combustion air stream entering into the burner; means for injection of fuel into the combustion air stream including at least one first fuel line with first fuel injection openings arranged in a plane perpendicular to the longitudinal burner axis; wherein the first fuel injection openings are configured and arranged so that an injection angle of the first fuel injection openings varies relative to the axial direction, relative to the radial direction, or both, about the circumference of the burner. 2. A burner comprising: a longitudinal burner axis; a swirler for a combustion air stream, the swirler including at least one combustion air inlet opening for the combustion air stream entering into the burner; means for injection of fuel into the combustion air stream comprising at least one first fuel line with first fuel injection openings arranged in a plane perpendicular to the longitudinal burner axis and distributed about the circumference of the burner; at least some of the first fuel injection openings being arranged in one or more first groups of closely spaced fuel injection openings so that each of the first groups generates a fuel jet with a large jet cross section. 3. A burner according to claim 1, wherein at least some of the first fuel injection openings are arranged in at least one first group of closely spaced fuel injection openings so that each of the at least one first group generates a fuel jet with a large jet cross section. 4. A burner according to claim 2 or 3, wherein at least some of the at least one first group of first fuel injection openings differ by having varying opening diameters of the fuel injection openings. 5. A burner according to claim 4, wherein remaining first fuel injection openings that are not arranged in said at least one first groups have a smaller opening diameter than the first fuel injection openings that are arranged in said at least one first groups. 6. A burner according to claim 1 or 2, wherein the injection angle of the first fuel injection openings alternates relative to the axial direction about the circumference between at least two values. 7. A burner according to claim 1 or 2, wherein the opening diameter of the first fuel injection openings alternates about the circumference between at least two values. 8. A burner according to claim 1 or 2, wherein a first set of said first fuel injection openings have a larger injection angle relative to the axial direction and have a larger opening diameter than a second set of said first fuel injection openings with a smaller injection angle. 9. A burner according to claim 1 or 2, wherein the injection angle relative to the radial direction is selected such that fuel jets of differing second groups exiting from the first fuel injection openings each intersect in different points outside a central burner axis. 10. A burner according to claim 1 or 2, wherein the first fuel injection openings are arranged distributed about the circumference of the burner at an end of the burner facing the combustion chamber. 11. A burner according to claim 10, wherein the first fuel injection openings are arranged in one row. 12. A burner according to claim 1 or 2, wherein the at least one first fuel line is mechanically decoupled from the swirler. 13. A burner according to claim 12, wherein the at least one first fuel line with the first fuel injection openings form a first element that encompasses the swirler, and wherein the swirler comprises openings at an end facing the combustion chamber configured and arranged for access of the first injection openings to an inner volume of the burner. 14. A burner according to claim 13, further comprising: connecting straps; and wherein the first element is connected via the connecting straps to the swirler. 15. A burner according to claim 1 or 2, wherein the at least one first fuel line comprises an annular slot extending on the circumference of the swirler. 16. A burner according to claim 1 or 2, wherein the at least one first fuel line with the first fuel injection openings is arranged along the axial direction on the swirler. 17. A burner according to claim 1 or 2, further comprising: at least one second fuel line including second fuel injection openings extending along the axial direction, arranged on the swirler. 18. A burner according to claim 17, wherein the at least one first fuel line has a cross section configured and arranged to permit a higher volume flow than that of the at least one second fuel line. 19. A burner according to claim 17, further comprising: an inner volume; an inner body arranged in the inner volume; wherein the second fuel injection openings of the at least one second fuel line are arranged along the axial direction and distributed on the inner body. 20. A burner according to claim 17, wherein the second fuel injection openings are formed such that the opening diameter of the second fuel injection openings, an injection angle of the second fuel injection openings, or both, varies relative to the axial direction, the radial direction, or both, along the fuel lines, about the circumference of the burner, or both. 21. A burner according to claim 17, wherein at least some of the second fuel injection openings are arranged in at least one third group of closely spaced fuel injection openings so that each of the at least one third group generates a fuel jet with a large jet diameter. 22. A burner according to claim 17, further comprising: means for independently controlling the premix fuel supply to the at least one first fuel line and to the at least one second fuel line. 23. A burner according to claim 1 or 2, wherein the swirler comprises a swirler grid. 24. A burner according to claim 1 or 2, wherein the combustion air inlet openings comprise tangential inlet slots extending in an axial direction. 25. A method for operating a burner, the method comprising: providing a burner according to claim 17; and supplying synthesis gas via the at least one first fuel line; and supplying natural gas via the at least one second fuel line. 26. A burner according to claim 1 or 2, wherein the first fuel injection openings are arranged at an end of the burner facing a combustion chamber and are distributed about the circumference of the burner. 27. A gas turbine comprising: at least one burner according to claim 1 or 2.
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이 특허에 인용된 특허 (7)
Dbbeling Klaus (Nussbaumen CHX) Knpfel Hans P. (Besenbren CHX) Polifke Wolfgang (Windisch CHX) Sattelmayer Thomas (Mandach CHX), Burner for operating an internal combustion engine, a combustion chamber of a gas turbine group or firing installation.
Joshi Narendra D. (Cincinnati OH) Angel Paul R. (Fairfield OH) Caldwell James M. (Alexandria KY) Heberling Paul V. (Cincinnati OH) Dean Anthony J. (Scotia NY), Dual fuel mixer for gas turbine combustor.
Carroni, Richard; Bernero, Stefano; Biagioli, Fernando; Lachaux, Thierry, Method for combusting hydrogen-rich, gaseous fuels in a burner, and burner for performing said method.
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