Abstract: A lance is presented for introducing fuel into a second burner of a combustion chamber of a gas turbine installation with sequential combustion, having a first and a second combustion chamber. The lance includes a foot and a shank which projects from it. In an installed state of the lance the foot extends perpendicularly or at an angle to a main flow direction of the burner. The shank extends centrally in the burner and generally parallel to the main flow direction. At least one projecting arm, having at least one nozzle for introducing fuel, is arranged such that it extends from the shank. A respective end of the at least one arm is oriented in the main flow direction and extends generally parallel to the main flow direction.

Abstract: A lance is presented for introducing fuel into a second burner of a combustion chamber of a gas turbine installation with sequential combustion, having a first and a second combustion chamber. The lance includes a foot and a shank which projects from it. In an installed state of the lance the foot extends perpendicularly or at an angle to a main flow direction of the burner. The shank extends centrally in the burner and generally parallel to the main flow direction. At least one projecting arm, having at least one nozzle for introducing fuel, is arranged such that it extends from the shank. A respective end of the at least one arm is oriented in the main flow direction and extends generally parallel to the main flow direction.

Abstract: A method for operating a combustion chamber (1) for a gas turbine. The combustion chamber (1) has a combustion space (2) and a plurality of burners (3), which are each arranged at an inlet (13) of the combustion space (2). The burners (3) are divided into two burner groups (4I, 4II). A common oxidant supply (5) is provided for all the burners (3). A common first fuel supply (7) is provided for the burners (3I) belonging to the first burner group (4I). A common second fuel supply (9) and a common additional fuel supply (11) are provided for the burners (3II) belonging to the second burner group (4II). A first fuel stream (8) is fed to the burners (3I) belonging to the first fuel group (4I), in such a manner that a lean fuel/oxidant mix is established. A second fuel stream (10) is fed to the burners (3II) belonging to the second burner group (4II) in such a manner that a lean fuel/oxidant mix is established.

Abstract: A method for operating a combustion chamber (1) for a gas turbine. The combustion chamber (1) has a combustion space (2) and a plurality of burners (3), which are each arranged at an inlet (13) of the combustion space (2). The burners (3) are divided into two burner groups (4I, 4II). A common oxidant supply (5) is provided for all the burners (3). A common first fuel supply (7) is provided for the burners (3I) belonging to the first burner group (41). A common second fuel supply (9) and a common additional fuel supply (11) are provided for the burners (3II) belonging to the second burner group (4II). A first fuel stream (8) is fed to the burners (3I) belonging to the first fuel group (4I), in such a manner that a lean fuel/oxidant mix is established. A second fuel stream (10) is fed to the burners (3II) belonging to the second burner group (4II) in such a manner that a lean fuel/oxidant mix is established.