Method for combusting hydrogen-rich, gaseous fuels in a burner, and burner for performing said method

1. A method for combustion of a hydrogen-rich, gaseous fuel in combustion air in a double-cone burner of a gas turbine, the method comprising:

injecting the hydrogen-rich, gaseous fuel at least partially isokinetically with respect to the combustion air such that the hydrogen-rich, gaseous fuel is injected at least partially in the same direction and at least partially at the same velocity as the combustion air,

wherein the hydrogen-rich, gaseous fuel is injected into the combustion air through one or more elongated rounded openings,

wherein a main axis of each of the elongated rounded openings is oriented parallel to a local air flow, and

wherein the hydrogen-rich, gaseous fuel is injected through the elongated rounded openings at a slant that, in relation to a vertical of a vortex air flow, is oriented in a direction of the vortex air flow.

2. The method according to claim 1 , wherein the slant is≧20°.

3. The method according to claim 1 , wherein a ratio of the main axis to a secondary axis of the elongated rounded openings is greater than 2:1.

4. The method according to claim 1 , wherein a cross-sectional surface area of the elongated rounded openings corresponds to a cross-sectional surface area of circular openings having a diameter between 2 mm and 6 mm.

5. The method according to claim 1 , wherein a wall of the burner is effusion-cooled directly downstream from the elongated rounded openings by a plurality of effussion holes.

6. The method according to claim 1 , wherein the combustion air enters an interior of the double-cone burner through air slits of a double cone and forms therein a vortex air flow in an area of the double cone.

7. The method according to claim 6 , wherein elongated rounded openings are disposed in a vicinity of an outlet of the double cone.

8. The method according to claim 6 , wherein at least a part of the hydrogen-rich, gaseous fuel is injected into the vortex air flow through elongated rounded openings in a fuel lance that projects into the interior of the double cone in an axial direction.

9. The method according to claim 6 , wherein a mixing tube is disposed in an axial direction downstream from the double cone, the hydrogen-rich, gaseous fuel being injected into the vortex air flow through elongated rounded openings in a wall of the mixing tube.

10. The method according to claim 6 , wherein the hydrogen-rich, gaseous fuel is injected isokinetically with respect to the combustion air such that the hydrogen-rich, gaseous fuel is injected in the same direction and at the same velocity as the combustion air.

11. The method according to claim 10 , wherein the combustion air enters the interior of the double cone through air slits in the double cone, the hydrogen-ria, gaseous fuel being injected isokinetically into the combustion air entering the interior of the double cone in an area of the air slits.

12. The method according to claim 11 , wherein the injecting the hydrogen-rich, gaseous fuel is performed using a comb injector.

13. The method according to claim 11 , wherein the injecting the hydrogen-rich, gaseous fuel is performed using a piggyback injector disposed on top of the double cone.

14. A double-cone burner for combustion of a hydrogen-rich, gaseous fuel in a gas turbine, comprising:

an injection unit configured to at least partially isokinetically inject the hydrogen-rich, gaseous fuel into combustion air flowing through the double-cone burner,

wherein the injection unit is connected to a fuel source at supplies the hydrogen-rich, gaseous fuel,

wherein the injection unit comprises an elongated rounded opening, and

wherein a main axis of the elongated rounded opening is oriented parallel to a local air flow.

15. The burner according to claim 14 , wherein the injection unit comprises a perforation, a hole, or a perforation and a hole configured to convey the hydrogen-rich, gaseous fuel through a wall of the burner to elongated rounded openings that are configured with a slant to a normal of the burner wall, such that the hydrogen-rich, gaseous fuel is injected through the elongated rounded openings at a slant of≧20° that in relation to a vertical of a vortex air flow, is oriented in a direction of the vortex air flow.

16. The burner according to claim 14 , wherein a ratio of the main axis to a secondary axis of the elongated rounded opening is greater than 2:1.

17. The burner according to claim 14 , wherein a cross-sectional surface area of the elongated rounded opening corresponds to a cross-sectional surface area of a circular opening having a diameter between 2 mm and 6 mm.

18. The burner according to claim 14 , wherein the elongated rounded opening is configured as an ellipse, oval, or slot.

19. The burner according to claim 14 , wherein the injection unit is disposed in a vicinity of an outlet of a double cone of the burner or a vicinity of a mixing tube that adjoins the double cone.

20. The burner according to claim 14 , wherein a double cone of the burner includes air slits configured to allow the combustion air to enter an interior of the double cone, the injection unit including a plurality of tangentially oriented fuel nozzles disposed in an area of the air slits.

21. The burner according to claim 20 , wherein the fuel nozzles are part of a comb injector.

22. The burner according to claim 20 , wherein the fuel nozzles are part of a piggyback injector disposed on top of the double cone.

23. The burner according to claim 14 , wherein the injection unit includes a fuel lance that projects into an interior of a double cone of the burner and elongated rounded openings disposed in an axial direction.

24. The burner according to claim 14 , wherein a wall of the burner is effusion-cooled directly downstream from the elongated rounded opening by a plurality of effusion holes.