Method for operating a burner arrangement of a gas turbine
A method for operating a burner arrangement of a heat engine, particularly a gas turbine, having a plurality of burners, each having at least one pilot burner and main burner, in which method, on the basis of a preset operation of the heat engine, the total quantity of fuel supplied to the burners is maintained substantially constant in a load-controlled manner: in a first group of burners, for each burner, both the pilot burner as well as the main burner are supplied with fuel; in a second group of burners, the fuel supply to the main burners is interrupted, while the pilot burners continue to be operated; and the fuel quantity remaining as a result of the interruption of the fuel supply to the main burners of the second group is redistributed to the still active main burners of the first group. CO emissions are reduced as a result.
1. A method for operating a burner arrangement of a heat engine or of a gas turbine, having a plurality of burners, each comprising at least one pilot burner and at least one main burner, wherein, on the basis of a preset operation of the heat engine, in a load-controlled manner, the method comprising:
maintaining a total quantity of fuel supplied to the burners substantially constant,
in a first group of burners, in each burner, supplying both the pilot burner and the main burner with fuel,
in a second group of burners, interrupting the fuel supply to the main burners, wherein the pilot burners continue to be operated, and
redistributing the quantity of fuel remaining as a result of the interruption in the fuel supply to the main burners of the second group to the main burners of the first group which are still active.
2. The method as claimed in claim 1 , further comprising:
in a third group of burners, interrupting the fuel supply both to the main burners and to the pilot burners, and redistributing the remaining quantity of fuel to the main burners in the first group which are still active.
3. The method as claimed in claim 2 ,
wherein a maximum of 30% of the burners are included in the third group.
4. The method as claimed in claim 1 ,
wherein a maximum of 40% of the burners are included in the second group.
5. The method as claimed in claim 1 ,
wherein the pilot burners of the burners in the second group are operated with a lower air ratio than the pilot burners in the first group.
6. The method as claimed in claim 1 ,
wherein a number of burners with an at least partially interrupted fuel supply is varied, in accordance with the capacity of the heat engine.
7. The method as claimed in claim 1 ,
wherein the main burners are operated in premix mode.
8. The method as claimed in claim 1 ,
which is applied at a power output which lies below the rated capacity of the heat engine.
9. A combustion system for a heat engine, comprising:
a burner arrangement having a plurality of burners, each of which comprises at least one pilot burner and at least one main burner,
an auxiliary system for the supply of fuel to the burners, and
a controller, which is configured to:
maintain a total quantity of fuel supplied to the burners substantially constant,
in a first group of burners, in each burner, supply both the pilot burner and the main burner with fuel,
in a second group of burners, interrupt the fuel supply to the main burners, wherein the pilot burners continue to be operated, and
redistribute the quantity of fuel remaining as a result of the interruption in the fuel supply to the main burners of the second group to the main burners of the first group which are still active.
10. The combustion system as claimed in claim 9 , further comprising:
a third group of burners,
wherein, between a burner in the first group and a burner in the third group, at least one burner in the second group is arranged.
11. The combustion system as claimed in claim 10 , further comprising:
separate fuel lines to the pilot burners and main burners, wherein shut-off devices are at least installed in the fuel lines to the main burners in the second group and the third group.
12. The combustion system as claimed in claim 9 , wherein the main burners are configured as premix burners.
13. The combustion system as claimed in claim 9 ,
wherein the auxiliary system comprises a first subsystem and a second subsystem, wherein the first subsystem is designed for the supply of the main burners and the pilot burners in the first group, and the second subsystem is designed for the supply of the pilot burners in the second group.
14. The combustion system as claimed in claim 9 ,
wherein the burner arrangement is configured as an annular combustion chamber.
15. A heat engine, comprising:
a combustion system as claimed in claim 9 .
16. The heat engine of claim 15 ,
wherein the heat engine comprises a gas turbine.