Gas turbine with sequential combustion arrangement
View Patent ↗The present disclosure refers to a method for operating a gas turbine with sequential combustors having a first-burner, a first combustion chamber, and a second combustor arranged sequentially in a fluid flow connection. To minimize emissions and combustion stability problems during transient changes when the fuel flow to a second combustor is initiated the method includes the steps of increasing the second fuel flow to a minimum flow, and reducing the first fuel flow to the first-burner of the same sequential combustor and/or the fuel flow to at least one other sequential combustor of the sequential combustor arrangement in order keep the total fuel mass flow to the gas turbine substantially constant. Besides the method a gas turbine with a fuel distribution system configured to carry out such a method is disclosed.
1. A gas turbine, comprising:
a compressor;
a sequential combustor arrangement having a plurality of sequential combustors, each sequential combustor including,
a first-burner with a first fuel injection,
a first combustion chamber,
a second combustor with a second fuel injection,
a second reaction zone arranged sequentially in a fluid flow connection, and
a fuel distribution system for supplying fuel to the first fuel injection and to the second fuel injection, the fuel distribution system including a fuel control valve and a fuel ring main for supplying fuel to the first fuel injection; and
a turbine downstream of the sequential combustor arrangement,
wherein at least one supply line to the second fuel injection is branched off downstream of the fuel control valve for supplying fuel to the first fuel injection, and in that a second fuel control valve is arranged in the at least one supply line to the second fuel injection.
2. The gas turbine as claimed in claim 1 , wherein the sequential combustor arrangement comprises:
a first group of first-burners connected to a first first-burner group fuel ring main;
a second group of first-burners connected to a second first-burner group fuel ring main;
a first group of a second fuel injectors connected to a first sequential-group fuel ring main; and
a second group of second fuel injectors connected to a second sequential-group fuel ring main;
wherein a first-burner group fuel control valve is arranged in a supply line to the first first-burner group fuel ring main,
a second burner group fuel control valve is arranged in a supply line to the second first-burner group fuel ring main,
a supply line for the first sequential-group fuel ring main is branched off downstream of the first first-burner group fuel control valve, and a first sequential-group fuel control valve is arranged in the supply line for the first sequential-group fuel ring main, a supply line for the second sequential-group fuel ring main is branched off downstream of the second first-burner group fuel control valve, and a second sequential-group fuel control valve is arranged in the supply line for the second sequential-group fuel ring main,
and wherein each second fuel injector of the first group of second fuel injectors is arranged downstream of one first-burner of the first group of first-burners in one sequential combustor.
3. The gas turbine as claimed in claim 1 , wherein the sequential combustor arrangement comprises
a first group of first-burners connected to a first first-burner group fuel ring main,
a second group of first-burners connected to a second first-burner group fuel ring main,
a first group of a second fuel injectors connected to a first sequential-group fuel ring main,
and a second group of second fuel injectors connected to a second sequential-group fuel ring main,
wherein a first-burner group fuel control valve is arranged in a supply line to the first first-burner group fuel ring main,
a second burner group fuel control valve is arranged in a supply line to the second first-burner group fuel ring main,
a supply line for the first sequential-group fuel ring main is branched off downstream of the first first-burner group fuel control valve, and a first sequential-group fuel control valve is arranged in the supply line for the first sequential-group fuel ring main, a supply line for the second sequential-group fuel ring main is branched off downstream of the second first-burner group fuel control valve, and a second sequential-group fuel control valve is arranged in the supply line for the second sequential-group fuel ring main,
and wherein each second fuel injector of the first group of a second fuel injectors is arranged downstream of one first-burner of the second group of first-burners in one sequential combustor.
4. The gas turbine as claimed in claim 1 , wherein each second fuel injector of the sequential combustor arrangement is connected to a supply line branched off downstream of the second first-burner group fuel control valve and having a fuel feed including an injector fuel control valve.